A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.
F02C 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
F02K 3/077 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux l'ensemble fonctionnel étant du type multi-flux, c.-à-d. ayant au moins trois flux
2.
SEAL COMPRISING A SUCCESSION OF ZONES WITH AND WITHOUT ANTI-FRICTION COATINGS
A seal is configured to be arranged between a first element and a second element of a propulsion assembly. The seal includes a longitudinal sector designed to be in contact with the second element, wherein the longitudinal sector is formed of an elastic leak-tight material and includes a first zone having an anti-friction coating, a second zone having a leak-tight coating, and a third zone having an anti-friction coating. The first, second and third zones arranged side by side and extend longitudinally from a first end to a second end of the longitudinal sector.
The invention relates to a thrust-reversal system for an aircraft turbojet engine (2), the thrust-reversal system (18) delimiting a secondary duct (16a), comprising an internal fixed structure (160) and an external fixed structure (162) connected together at at least one bifurcation (164, 166) delimited on either side by a wall (16a, 160b) of the internal fixed structure (160), the system comprising: at least one mobile cowl (20), which can move between a retracted position, and a deployed position; a set of air deflection devices; at least one sealing membrane (24), which can move between a retracted position and a deployed position; the sealing membrane (24) being attached to at least one fixed attachment element relative to the external fixed structure (162) and, at the front attachment points (240), to deployment devices (26, 28); the deployment devices (26, 28) comprising, for the or for each sealing membrane, at least a first and a second traction cable (28), each traction cable (28) being connected to the sealing membrane and to a drawing system (30), the drawing system (30) making it possible to pull on the traction cables during the deployment of the thrust-reversal device.
F02K 1/76 - Commande ou régulation des inverseurs de poussée
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
4.
PROPULSION ASSEMBLY FOR AN AIRCRAFT, COMPRISING AN INTERMEDIATE COWL OF THE STATIONARY, REMOVABLE TYPE, MOUNTED ON A HINGE SYSTEM
An aircraft propulsion unit including a nacelle comprising a fan compartment, a front cowling forming an air inlet, and an intermediate section having at least one removable fixed intermediate cowling, externally delimiting the fan compartment, and attached to another structure of the propulsion unit by removable through fasteners. The intermediate cowling is connected to another element of the propulsion unit by means of a hinge system which, as a result of removing the removable through fasteners, is designed to allow the intermediate cowling to be moved between a closed position, in which it extends continuously with the front cowling, and an open position, in which the intermediate cowling is shifted upstream or downstream so as to open the fan compartment
F02K 7/00 - Ensembles fonctionnels dans lesquels le fluide de travail est utilisé uniquement sous forme de jet, c.-à-d. ensembles ne comportant ni turbine ni autre moteur entraînant un compresseur ou une soufflante carénéeLeur commande
B64D 27/16 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
F02C 7/042 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction à géométrie variable
The invention relates to a method for manufacturing a composite panel comprising a cellular core positioned between two skins, comprising the following steps: positioning a first resin layer (4) on a first mould (2); positioning a cellular-structure element (6) which has a cellular structure (8) arranged between two fibrous preforms (10, 12) intended to form the skins, a first of the fibrous preforms being positioned on the first resin layer; positioning a second resin layer (14) on the second of the fibrous preforms or on a second mould; positioning one or the second mould, the first mould and the second mould being arranged relative to one another such that the two moulds can move relative to one another; curing under vacuum, causing the resin to permeate the cellular-structure element and the two moulds to move relative to one another.
B29C 70/02 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant des combinaisons de renforcements et de matières de remplissage dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées ou non remplies
B29C 43/20 - Fabrication d'objets multicouches ou polychromes
B29C 43/36 - Moules pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 70/42 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/46 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs"
B29C 70/86 - Incorporation dans des couches de renforcement imprégnées cohérentes
B29D 24/00 - Fabrication d'objets avec parois creuses
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B32B 5/24 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse
B32B 37/14 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches
6.
THRUST-REVERSAL SYSTEM FOR AN AIRCRAFT TURBOJET ENGINE, NACELLE AND PROPULSION UNIT COMPRISING SUCH A SYSTEM
The invention relates to a thrust-reversal system comprising: at least one movable cowl (20), movable between a retracted position and a deployed position; a set of air deflection devices (22); at least one shut-off device (24) for shutting off the secondary duct (16a) and movable between a retracted position corresponding to the retracted position of the movable cowl (20), in which position the shut-off device is at least partially housed in a space (200) provided in the movable cowl (20), and a deployed position corresponding to the deployed position of the movable cowl (20), in which position the shut-off device (24) is at least partially deployed into the secondary duct (16a), so as to deflect a majority portion of the secondary airflow towards the air deflection devices (22); the thrust-reversal system comprising at least one deployable membrane (22, 24), the deployable membrane (22, 24) comprising at least one reinforcement.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
The invention relates to an aircraft propulsion assembly (1) extending along a longitudinal axis (X) and comprising a turbine engine (2), a pylon (3) that connects the turbine engine (2) to the wing of the aircraft, an inner fairing (4) that surrounds the turbine engine (2), and an outer fairing (5) that circumferentially surrounds the inner fairing (4) and that comprises a right hollow cowl (10A) having an internal space and a left hollow cowl (10B) having an internal space, which cowls are capable of moving between a closed position and an open position. Each of the cowls (10A, 10B) comprises an upper part (20A, 20B) which is located below the pylon (3) when the cowl is in the closed position and the internal space of which forms an upstream flow path (V2A, V2B) that widens laterally from upstream to downstream, and further comprises a lower part (30A, 30B) that circumferentially extends the upper part (20A, 20B) downwards when the cowl is in the closed position, and the internal space of the lower part (30A, 30B) of each of the cowls (10A, 10B) forms a downstream flow path (V3A, V3B) that extends the upstream flow path (V2A, V2B).
An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. The exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.
A gripper for gripping a honeycomb-shaped part and depositing the part on a target surface includes gripping elements mounted on a support, each of the gripping elements being configured to be inserted into an internal cell of the honeycomb-shaped part. The gripping elements include a gripping surface that is laterally moveable relative to the support so as to come into contact with a side wall element of the internal cell.
A method for manufacturing a multi-perforated acoustic skin out of composite material for an acoustic attenuation structure, the method including forming a fibrous preform including a matrix precursor material, carrying out a heat treatment for transforming the precursor into a matrix so as to obtain a multi-perforated acoustic skin made of composite material including a fibrous reinforcement densified by the matrix, the forming of the fibrous preform including draping fibers on a surface of a mandrel including protuberances, and the mandrel and the protuberances can be each made of a material that melts at a temperature lower than the heat-treatment temperature for transforming the precursor into a matrix in such a way as to eliminate the mandrel and the protuberances during the transforming heat treatment step.
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29K 105/10 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils orientés
The invention relates to a propulsion assembly (1) comprising a turbomachine having a longitudinal axis, a nacelle, a first element (E1), a second element (E2) movable in translation with respect to the first element in a direction parallel to the longitudinal axis between a first and a second position and a fluidic circuit (70), the nacelle comprising at least one element from among the first and second elements, the propulsion assembly being characterized in that: the fluidic circuit (70) comprises a first duct (71) and a second duct (72) secured respectively to the first and second elements and respectively comprising first and second interlocking connectors (73, 74) configured to cooperate with one another so as to allow the fluid to flow between the first and second ducts when the second element is in the first position and to prevent the flow of the fluid when the second element is in the second position.
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
12.
SURFACE HEAT EXCHANGER COMPRISING A PRESSURE LOSS REDUCER AND AIRCRAFT NACELLE PROVIDED WITH SUCH A HEAT EXCHANGER
The invention relates to a heat exchanger (20), in particular for an aircraft nacelle, comprising a first skin (21) and a second skin (22) joined together, and a plurality of channels (23) for distributing a hydraulic fluid (F1) arranged between the first skin (21) and the second skin (22), wherein the exchanger further comprises a first hydraulic interface (24) and a second hydraulic interface (29) for the hydraulic fluid. The exchanger (20) further comprises at least one pressure loss reduction member (40) extending axially towards the first hydraulic interface (24) or the second hydraulic interface (25), wherein the pressure loss reduction member (40) has a generally conical cross-section.
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
F28D 3/02 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, dans lesquels l'autre source de potentiel calorifique s'écoule sous forme de pellicule continue ou ruisselle librement sur les canalisations avec canalisations tubulaires
The invention relates to a hydraulic control device (10) for a thrust reverser (12) of an aircraft propulsion assembly nacelle, this device (10) comprising: a hydraulic motor (26), a first solenoid valve (28), referred to as the isolation solenoid valve, comprising a fluid inlet (28a) capable of being connected to a fluid source (24) of an aircraft, a fluid discharge line (34) fitted with a check valve (32), and a hydraulic circuit (36) for connecting the motor (26) to the isolation solenoid valve (28) and to the discharge line (34).
The invention relates to a hydraulic control device (10) for a thrust reverser (12) of an aircraft propulsion assembly nacelle, this device (10) comprising: - a hydraulic motor (26); - a first solenoid valve (28), referred to as the isolation solenoid valve, comprising a fluid inlet (28a) capable of being connected to a fluid source (24) of an aircraft; - a fluid discharge line (34) fitted with a check valve (32); - and a hydraulic circuit (36) for connecting the motor (26) to the isolation solenoid valve (28) and to the discharge line (34).
The invention relates to an acoustic panel (17) comprising at least: - a first box (18) comprising a first cellular structure (20) that comprises acoustic cells open at least at one of their ends, and a first porous acoustic structure (22) arranged on the first cellular structure (20) and closing off the end of the acoustic cells; - a second box (19) comprising a second cellular structure (21) that comprises acoustic cells that are open at least at one of their ends and a second porous acoustic structure (23) arranged on the second cellular structure (21) and closing off the end of the acoustic cells, wherein the first and second boxes (18, 19) are arranged next to one another and attached to one another, characterised in that the first porous acoustic structure (22) at least partially covers the second cellular structure (21) in a region of overlap (30).
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
The invention relates to an air inlet (1) for an aircraft turboprop (20) comprising an intake duct (2) for an air flow which leads, at a bifurcation (5), into a supply duct (3) to a turbine (25) and into an ejection duct (4) for ejecting foreign bodies from the air flow, the air inlet further comprising a heat exchanger (7) for cooling a heat transfer fluid, wherein a closure member (8) is controllable at the bifurcation (5) to assume: - a stowed position (P0) in which the air flow passes through the ejection duct (4) from the bifurcation (5) to a discharge outlet (6), a first deployed position in which the closure member (8) completely obstructs the ejection duct (4), and a second deployed position in which the closure member (8) partially obstructs the intake duct (2) in order to draw a reverse air flow into the ejection duct (4) when the aircraft is on the ground.
The invention relates to a thrust reverser for an aircraft propulsion unit, comprising a mobile structure (29) comprising at least one reverser cowl (33) having a cavity (54) open at the upstream end and delimited between a radially outer wall (50) and a radially inner wall (52) of the reverser cowl (33), the reverser also comprising a membrane (58) for shutting off the secondary flow path (21B), as well as a membrane-deployment member (62) connected to this membrane (58), and designed to be arranged at least partially in the secondary flow path (21B) when the mobile structure occupies its retracted thrust-reversal position. According to the invention, when the mobile structure (29) occupies its advanced forward-thrust position, the membrane-deployment member (62), in the form of a connecting rod, is at least partially housed in the cavity (54) of the mobile reverser cowl (33).
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/76 - Commande ou régulation des inverseurs de poussée
18.
THRUST REVERSER WITH SEALING MEMBRANE AND RETENTION SYSTEM
The invention relates to a thrust reverser (1) for an aircraft propulsion unit, the thrust reverser (1) comprising a stationary structure (3), a movable structure (13) that is translatable with respect to the stationary structure (3) between a thrust position and a thrust reversal position, at least one sealing membrane (17) designed to deflect at least part of the secondary flow towards the outside, at least one retention system (21) designed to engage with the stationary structure (3) and the corresponding sealing membrane (17), the retention system (21) being configured to subject the corresponding sealing membrane (17) to a return force comprising a component opposite to the general direction of flow in the thrust reversal position.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/76 - Commande ou régulation des inverseurs de poussée
19.
METHOD FOR JOINING TWO ANODISED ELEMENTS BY FRICTION STIR WELDING
The present application describes a method for joining two anodized elements by friction stir welding. This method for joining a first element to a second element comprises a step of anodizing the first element, a step of anodizing the second element, and a step of producing a weld seam by friction stir welding the first element to the second element.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
B23K 20/233 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage tenant compte des propriétés des matériaux à souder sans couche ferreuse
A propulsion assembly for an aircraft equipped with a thrust reverser comprising an actuator for moving a movable structure between an advanced direct thrust position and a retracted thrust reversal position, the propulsion assembly further comprising an actuator support device equipped with a first connecting part for connecting it to the deflection edge and/or to the outer shell of the intermediate casing, with a second connecting part for connecting it to a body of the actuator, and with a central part running axially between the shell and the actuator. Moreover, the actuator support device forms a guide for a set of cascades of the movable structure.
F02K 1/76 - Commande ou régulation des inverseurs de poussée
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
21.
THRUST REVERSER COMPRISING AN IMPROVED SAFETY SYSTEM FOR DEPLOYING A MEMBRANE FOR SEALING OFF THE SECONDARY FLOW PATH
The invention relates to a thrust reverser for an aircraft propulsion assembly, comprising a membrane for sealing off a secondary flow path, and at least one connecting rod for deploying this membrane, which is designed to be moved from a first position in which it projects radially into the secondary flow path, when the mobile structure occupies its advanced direct-thrust position, to a second position in which it is folded down in the downstream direction, when the mobile structure occupies its retracted thrust-reversal position. According to the invention, the reverser also comprises a device (70) for actuating the connecting rod (62), equipped with a safety system (120) for limiting the risks of poor kinematics.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/76 - Commande ou régulation des inverseurs de poussée
An acoustic panel comprising a first group of cavities oriented towards a front end of the panel and a second group of cavities oriented towards a rear end of the panel.
B32B 15/092 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique comprenant des résines époxy
B32B 15/20 - Produits stratifiés composés essentiellement de métal comportant de l'aluminium ou du cuivre
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
23.
AIR FLOW EJECTOR NOZZLE WITH DETACHABLE INTERNAL STRUCTURE AND TURBINE ENGINE PROVIDED WITH SUCH A NOZZLE
The invention relates to a nozzle for ejecting a turbine engine air flow, in particular for an aircraft, the ejector nozzle extending firstly around a longitudinal axis (X) and secondly between an inlet cross-section and an outlet cross-section along the longitudinal axis (X), the ejector nozzle being delimited at least in part by an external structure (22) and an internal structure (23) having an axis of revolution centred on the longitudinal axis and at least partially forming a flow path. According to the invention, the internal structure (23) is removably mounted with respect to the external structure (22) and is removably attached to a radially inner shroud (25) extending axially downstream of the internal structure (23) and partially defining the outlet cross-section (21), and the internal structure comprises retaining means ensuring that a radial height (H2) of the outlet cross-section (21), during operation, remains fixed and constant.
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
F02K 3/02 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion
F02K 3/077 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux l'ensemble fonctionnel étant du type multi-flux, c.-à-d. ayant au moins trois flux
24.
AIR FLOW EJECTOR NOZZLE WITH A CONSTANT OUTLET CROSS-SECTION AND TURBINE ENGINE PROVIDED WITH SUCH A NOZZLE
The invention relates to a nozzle for ejecting a turbine engine air flow, in particular for an aircraft, the ejector nozzle extending firstly around a longitudinal axis (X) and secondly between an inlet cross-section (20) and an outlet cross-section (21) along the longitudinal axis (X), the ejector nozzle being delimited at least in part by a radially outer shroud (24) and a radially inner shroud (25) at least partially forming a flow path (18, 15). According to the invention, a plurality of struts (45) extend radially between the radially outer shroud (24) and the radially inner shroud (25), and the struts (45) are arranged regularly around the longitudinal axis (X) and have a predetermined height (H1) configured such that a radial height (H2) of the outlet cross-section (21), during operation, remains fixed and constant.
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
F02K 3/02 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion
F02K 3/077 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux l'ensemble fonctionnel étant du type multi-flux, c.-à-d. ayant au moins trois flux
25.
AIRFLOW EJECTION NOZZLE WITH CONSTANT OUTLET SECTION AND TURBINE ENGINE EQUIPPED WITH SUCH A NOZZLE
The invention relates to a turbine engine airflow ejection nozzle, in particular for an aircraft, the ejection nozzle extending about a longitudinal axis (X) and between an inlet section (20) and an outlet section (21) along the longitudinal axis (X), the ejection nozzle being at least partially delimited by a radially outer shroud (24) and a radially inner shroud (25) at least partially forming a flow path (18, 15). According to the invention, a plurality of struts (45) extend radially between the radially outer shroud (24) and the radially inner shroud (25), and the struts (45) are arranged evenly about the longitudinal axis (X) and have a predetermined height (H1) configured so that a radial height (H2) of the outlet section (21), during operation, is fixed and constant.
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
F02K 3/02 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion
F02K 3/077 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux l'ensemble fonctionnel étant du type multi-flux, c.-à-d. ayant au moins trois flux
26.
AIR FLOW EJECTOR NOZZLE WITH DETACHABLE INTERNAL STRUCTURE AND TURBINE ENGINE PROVIDED WITH SUCH A NOZZLE
The invention relates to a nozzle for ejecting a turbine engine air flow, in particular for an aircraft, the ejector nozzle extending firstly around a longitudinal axis (X) and secondly between an inlet cross-section and an outlet cross-section along the longitudinal axis (X), the ejector nozzle being delimited at least in part by an external structure (22) and an internal structure (23) having an axis of revolution centred on the longitudinal axis and at least partially forming a flow path. According to the invention, the internal structure (23) is removably mounted with respect to the external structure (22) and is removably attached to a radially inner shroud (25) extending axially downstream of the internal structure (23) and partially defining the outlet cross-section (21), and the internal structure comprises retaining means ensuring that a radial height (H2) of the outlet cross-section (21), during operation, remains fixed and constant.
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
F02K 3/02 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion
F02K 3/077 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux l'ensemble fonctionnel étant du type multi-flux, c.-à-d. ayant au moins trois flux
A de-icing system which includes actuators attached to the part; and a device for controlling the actuators in order to vibrate the part. The control device is designed for the following, the actuators being divided into a plurality of groups: to control the actuators of a first one of the groups in order to establish a resonant frequency of the part; then to control the actuators of a second one of the groups in order to establish a resonant frequency of the part and, in parallel, to control the actuators of the first group in order to de-ice the part by vibrating it, using the resonant frequency established with this first group.
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
28.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE MEMBRANE, HAVING LOW-MASS DEPLOYMENT MEANS
The invention relates to a thrust reverser for an aircraft propulsion assembly, the thrust reverser comprising a membrane (58) for closing the secondary duct, a second end of which membrane is connected to the inner wall of the secondary duct by a cable (62) that co-operates with an actuating device (70) for actuating this cable, wherein the device (70) comprises an elastic means (80) that co-operates with the second cable end (62b) of the deployment member (62), and wherein the reverser is configured such that, during an initial phase of the movement of the movable structure towards its retracted thrust reversal position, the elastic means (80) releases previously stored energy while urging the second cable end (62b), and such that, during a subsequent phase of this movement of the movable structure, the elastic means (80) stores energy while being urged by this second end (62b).
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/76 - Commande ou régulation des inverseurs de poussée
29.
THRUST REVERSER COMPRISING MOVABLE CASCADES AND A SEALING MEMBRANE
A thrust reverser for an aircraft propulsion assembly, including at least one sealing membrane designed to deflect at least one portion of the secondary flow towards a set of cascades when the movable structure of the reverser is in the retracted thrust reversal position, the reverser also including a first flexible hook connecting a first end of the membrane to the fixed structure of the reverser, a second hook connecting a second end of the membrane to the fixed structure or to the movable structure, the second hook being fixed to the radially inner delimiting wall of the secondary vein, or guided by an internal guide fixed to the same radially inner delimiting wall.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
30.
METHOD FOR PRODUCING A PART MADE OF COMPOSITE MATERIAL
A method for producing a part made of composite material, includes obtaining a mold includes (i) a fibrous texture, (ii) a granular filtration layer located between a drainage surface of the texture and a permeable discharge surface and including a powder of filtration particles, and (iii) an element for retaining the granular layer, which element is distinct from the layer and located between the permeable discharge surface and the drainage surface, introducing a suspension including matrix particles in a liquid medium through an introduction surface of the fibrous texture that is distinct from the drainage surface, the liquid medium passing through the drainage surface, the granular filtration layer and the retention element to be discharged through the permeable discharge surface, and the matrix particles being retained in the pores of the fibrous texture by the granular filtration layer, and forming the part made of composite material by forming a matrix.
B28B 1/26 - Fabrication d'objets façonnés à partir du matériau par coulée en moule poreux ou absorbant, c.-à-d. en coulant une suspension ou une dispersion du matériau dans un absorbeur de liquide ou un moule poreux, le liquide pouvant imbiber les parois du moule ou passer à travers celles-ci, p. ex. coulage de barbotineMoules à cet effet
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Steel buildings; metal tanks [structures]; common metals and
their alloys, including stainless steel; anti-friction
metal; extruded metal; white metal; sheet metal; steel
sheets; sheets of metal; forged metal parts; pressed metal
parts; steel; stainless steel; unwrought or semi-wrought
steel; alloys of common metals; aluminum; steel alloys. Machines for metal machining. Treatment of metals; metal treating, namely stamping,
forming, profiling, embossing, hydroforming; treatment of
metals by hydroforming based on explosives; providing metal
forming services by explosive-based hydroforming; metal
processing and shaping using the technique of hydroforming
based on explosives for production of metal parts complying
with particular specifications; customization and adaptation
of metal parts via hydroforming based on explosives for
third parties; heat treatment of metals; stamping services;
deep-drawing of metals; shaping of metal components; custom
assembly of materials for third parties; welding services;
machining of parts for third parties. Scientific, technical and industrial research relating to
materials and metals; research and development of new
products relating to materials and metals; technical
advisory services, engineering and expertise (engineering
work) in the field of materials and metals; machine and
material testing; material testing and analysis services;
design of technological demonstrators; engineering services
relating to metal forming systems; metal forming feasibility
study.
32.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE DEFLECTION MEMBRANE WITH IMPROVED ATTACHMENT
The invention relates to a deployable membrane (58) for closing off a secondary flow duct for a thrust reverser of an aircraft propulsion assembly, wherein the membrane extends in a circumferential direction (27) and comprises a membrane extension (70) configured so as to form a strap, a projecting portion of which comprises a first connecting section (70a) for attachment to the membrane, and a second connecting section (70b) intended to be connected to a membrane deployment element (62) located within the reverser, and wherein the strap comprises a transition zone (70c) arranged between its first connecting section (70a) having a first width (L1) in the circumferential direction (27), and its second connecting section (70b) having a second width (L2) strictly smaller than the first width (L1).
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
33.
DEVICE FOR HANDLING AN ELEMENT OF AN AIRCRAFT AND HANDLING ASSEMBLY PROVIDED WITH SUCH A DEVICE
The invention relates to a device (2) for handling an element (E) of an aircraft, the device comprising a shell (5) that is intended to surround the element, a cradle (6) defining a region for receiving the shell, and a support platform (13) on which the cradle is mounted, wherein the platform is capable of co-operating with a lifting system (3) of the device. The device comprises first means for adjusting the angular position of the cradle relative to the platform and second means for adjusting the position of the cradle along three degrees of freedom relative to three perpendicular axes, respectively.
A thrust reverser for an aircraft propulsion assembly, including a fixed structure equipped with at least one cascade as well as a radially inner delimiting wall of a secondary vein, and a movable structure including at least one reverser cowling, the cascade being arranged, in the forward direct thrust position, in a housing of the reverser cowling, and, in the retracted thrust reversal position, the wall reveals a passage opening of the secondary vein towards the cascade, the thrust reverser also including at least one sealing membrane designed to deflect at least one portion of the secondary flow. A hook is provided for securing the membrane to a rear cascade support frame, and to the radially inner delimiting wall of the secondary vein.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
35.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE DEFLECTION MEMBRANE HAVING A DESIGN THAT FACILITATES MAINTENANCE
The invention relates to a thrust reverser for an aircraft propulsion assembly, the reverser comprising two membrane support frames (60, 70) and a membrane support connecting rod (66) connected at its ends to the frames by two mechanical connections (67, 69), and a deployable deflection membrane (32), the reverser being configured such that, when the first mechanical connection (67) is in an attached state and the second mechanical connection (69) is in a detached state, the support connecting rod (66) can be brought into a maintenance configuration in which the second end (66b) of the connecting rod is located farther away from the second membrane support frame (60) than in the nominal configuration, thereby allowing relative movement of the membrane along the connecting rod in order to disengage it from the latter via the second end (66b) of the connecting rod.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
36.
METHOD FOR MANUFACTURING AN OPEN PART WITH REINFORCED RIBS
The invention relates to a method for manufacturing an open part (10) made of composite material and comprising a skin (12), ribs extending in an associated direction of extension, and at least one reinforced rib (14) having a reinforced head (22), the method comprising: - providing a first fibre preform (PF1) for forming the skin and the body of the ribs; - providing a second fibre preform (PF2) for forming the reinforced head of the reinforced ribs; - placing the assembly formed of the first and second fibre preforms in a moulding device (30) comprising a die (32) shaped to form the ribs of the part; and - thermocompressing the assembly to form the part; and the first preform comprises discontinuous fibres (PF12) for forming the body, while the second preform comprises continuous fibres oriented in the direction of extension.
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
37.
METHOD FOR PRODUCING A PART MADE OF COMPOSITE MATERIAL AND HAVING RAISED ELEMENTS, AND CORRESPONDING PART
The invention relates to a part (20) made of composite material for a turbine engine, in particular for an aircraft, the part comprising: - a composite skin (22) having an inner face (28) and an outer face (26), the composite skin comprising continuous fibres; and - at least one element (24) extending in an associated direction of extension (X), each element (24) comprising a body (30) extending from the inner face (28) of the skin to a free end (32) in a direction of elevation (Z) different from the direction of extension, each body (30) being connected to the inner face by at least one fillet (36, 36'), the body being made of a composite material predominantly comprising discontinuous fibres; characterised in that the part (20) further comprises an additional skin (40) of continuous fibres covering at least the at least one fillet for connecting the body to the inner face of the skin.
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29C 70/30 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
38.
PROPULSION ASSEMBLY WITH LONGITUDINAL LOCKING OF AT LEAST ONE NACELLE COVER
The invention relates to a propulsion assembly (1) for an aircraft, the assembly comprising: a turbine engine; a nacelle (5) having a section provided with at least one cover (7) that is movably mounted so as to deploy between a working position and a maintenance position for the purpose of providing access to a turbine engine (3); a pylon (11) suitable for attaching the turbine engine and/or the nacelle (5) to the aircraft; a longitudinal locking mechanism (19) comprising, for each cover (7), a finger (21) and a sleeve (23) provided with two retaining portions extending transversely to the corresponding longitudinal axis (17), wherein the finger (21) is configured so as to be guided between the two retaining portions in the maintenance position; and wherein the sleeve (23) is attached to the corresponding cover (7) or to an element connected to the corresponding cover (7), and the finger (21) is attached to the pylon (11), or vice versa.
An annular air intake lip for a nacelle of an aircraft propulsion assembly is provided. The annular lip can extend about an axis of revolution and include: an external annular wall, an internal annular wall, an upstream annular wall connecting the external and internal annular walls to define an annular cavity therebetween. At least part of the annular lip can include at least one heat transfer coating that is made from a carbon allotrope material.
A movable-cascade thrust reverser includes a multi-functional annular fixed structure configured to be rigidly connected to a turbine engine fan casing or to an intermediate casing secured to the fan casing
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
41.
SYSTEM FOR COOLING A LIQUID FOR LUBRICATING AN AIRCRAFT TURBOMACHINE
A system for cooling a liquid for lubricating an aircraft turbomachine, includes an exchanger including a cooling volume and a circuit for cooling a heat-transfer fluid by a loop for circulating the two-phase fluid, with thermocapillary pumping. The cooling circuit includes a condenser including channels connected in parallel to one another in order to make it possible to cool the fluid circulating in the condenser from a vapour state to a liquid state, a first capillary evaporator of the exchanger in order to absorb the heat of the lubricating liquid in the first volume, the first evaporator including a capillary porous wick for separating the heat-transfer fluid in the two-phase state between a liquid state and a gaseous state by a capillary pressure jump.
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
An electronic device for diagnosing the condition of a system of actuators of an aircraft turbine engine, the device being configured to be coupled to an electrical wiring harness of a turbine engine connecting a computer of a turbine engine to a system of actuators of the turbine engine, the device including a power supply block to power the device, a connection block configured to enable the connection of the device to the electrical wiring harness of the turbine engine to be diagnosed, a communication block configured to send information to a user and to receive instructions from the user, and a control block including a test signal transmission module and modules for measuring the signals received by the device in response to the test signals over a work cycle of the system of actuators of the turbine engine.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
G01R 31/28 - Test de circuits électroniques, p. ex. à l'aide d'un traceur de signaux
43.
REMOTE TRIGGERING OF A FIRE EXTINGUISHING OPERATION IN A FIRE ZONE OF A PROPULSION SYSTEM
An assembly for an aircraft propulsion system including a nacelle extending around a longitudinal axis and including an internal face that delimits, with an external face of the aircraft propulsion system, a fire zone, an extinguisher for extinguishing a fire in the fire zone, the extinguisher including a tank for containing an extinguishing agent, and a spraying nozzle for spraying the extinguishing agent out of the tank and into the fire zone, an activation device for activating the extinguisher, and a controller that transmits a control order to the activation device, the activation device receiving the control order and transmitting an activation order to the extinguisher, the activation order activating the extinguisher so as to cause the expulsion of the extinguishing agent via the nozzle. The extinguisher is mounted on the nacelle. The assembly includes one or more of a wireless communicator and a cable.
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
A62C 37/36 - Commande des installations de lutte contre l'incendie le signal de déclenchement étant émis par un détecteur distinct de la tuyère
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
44.
THRUST REVERSER GRILLE FOR AN AIRCRAFT NACELLE AND METHOD FOR PRODUCING SUCH A GRILLE
The invention relates to an air-deflecting grille (5) for an aircraft nacelle thrust reverser system, the grille (5) comprising at least two longitudinal members (6) extending in a longitudinal direction (L) of the grille, each longitudinal member (6) being connected to at least one adjacent longitudinal member by a plurality of vanes (7), the grille (5) comprising, at each of its longitudinal ends, an attachment flange extending in a transverse direction (T) of the grille (5) and being secured to end vanes connecting the corresponding ends of the longitudinal members (6), each longitudinal member (6) being formed from at least one fibrous ply (60) comprising: •- at least one first portion (600), or longitudinal portion (600), extending in the longitudinal direction (L) of the grille (5); and •- at least one second portion (602), or transverse portion (602), extending in the transverse direction (T) of the grille (5), so as to form at least a portion of at least one end vane.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
45.
INTEGRATING AN EXTINGUISHER INTO A "FIRE" ZONE OF A TURBOMACHINE
An assembly for an aircraft gas turbine engine includes a nacelle extending substantially around a longitudinal axis and including a fixed structure disposed around the aircraft gas turbine engine, the fixed structure including an internal surface suitable for delimiting with an external surface of the gas turbine engine a fire zone of the nacelle, a thermal protection covering the internal surface of the fixed structure of the nacelle at the level of the fire zone of the nacelle, and an extinguisher designed to extinguish a fire in the fire zone of the nacelle, the extinguisher including a tank suitable for containing an extinguishing agent. The tank is located between the thermal protection and the internal surface of the fixed structure of the nacelle.
F02C 7/25 - Prévention ou protection contre l'incendie
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
The invention relates to a cellular structure for an acoustic panel, the cellular structure comprising: - at least one acoustic cell comprising a cavity bounded by a peripheral wall; and - at least one first partition (24) arranged in the cavity to divide the cavity into two, the first partition (24) comprising a first acoustically permeable membrane (25), characterised in that the first partition (24) further comprises first lugs (26), each first lug (26) being received in a respective first slot formed in the peripheral wall to mechanically fasten the first partition (24) in the corresponding cavity.
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
47.
ASSEMBLY FOR AN EXHAUST CONE OF AN AIRCRAFT TURBOMACHINE
An assembly for an exhaust cone of an aircraft turbomachine, including a first annular wall, and first partitions and second partitions defining between them a plurality of acoustic boxes distributed around the first wall, an assembly formed by the first and the second partitions being fastened to the first wall with first fastening members arranged upstream and with second fastening members arranged downstream, the first fastening members being offset circumferentially with respect to the second fastening members.
An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.
An open composite panel for an aircraft includes a composite skin having an inner face and an outer face, and a plurality of stiffening ribs, each rib extending over the inner face of the skin in a respective direction of extension and projecting from the inner face to a top that is opposite said inner face. The plurality of ribs includes at least one reinforced rib, each reinforced rib having at least one elongate stiffening portion extending along the top of the reinforced rib, said stiffening portion including fibers extending substantially in the direction of extension of the reinforced rib.
The invention relates to an installation for assembling a core of a panel of a turbomachine, comprising: - a fairing (12) having an outlet slot (112) for an adhesive tape (106), - a first reel (104) for storing and dispensing the adhesive tape (106) to the outlet slot (112), the adhesive tape (106) being intended to be stored around the first reel (104) and having at least one contact face with a first protective film (114, 116), - a second reel (108, 110), for returning the first protective film (114), mounted outside the fairing (12), - the second reel (108, 110) being configured to wind up the protective film (114, 116) as the adhesive tape (106) is unwound from the first reel (104) towards the outlet slot (112).
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
B29C 65/50 - Assemblage d'éléments préformésAppareils à cet effet en utilisant des adhésifs utilisant des rubans adhésifs
51.
INSTALLATION FOR ASSEMBLING THE CORE OF A PANEL AND ASSOCIATED METHOD
The invention relates to an installation for assembling the core of a panel of an aircraft turbine engine, comprising a bonding system (100) comprising: - a member (102) for storing and dispensing the adhesive (25), and - a nozzle (104) for ejecting the adhesive (25), the nozzle (104) extending between a first open end (106) connected to the storing and dispensing member (102) and a second open opposite end (108) for discharging the adhesive (25), the nozzle (104) further comprising an internal passage (105) for the adhesive (25), extending between the first and second ends (106, 108).
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
The invention relates to an actuating device (1) for an aircraft thrust reverser system (3) comprising at least one thrust reverser device (2), the actuating device (1) comprising at least one motorized drive unit (10) situated on an upstream side of a first lost-motion lock (12a) and designed to actuate an input shaft (11) of this first lock (12a), the first lock being designed, when unlocked, to actuate an output shaft driving a flexible synchronization shaft (13) situated on a downstream side, and the actuating device (1) further comprising at least one first movable jack rod (14b) which is mechanically connected to the flexible synchronization shaft and secured to a movable element of the thrust reverser device (2), the first movable rod belonging to a first set of movable rods which is associated with the first lock (12a).
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/76 - Commande ou régulation des inverseurs de poussée
53.
MULTIAXIAL FIBRE SHEET COMPRISING METAL ELEMENTS FOR PRODUCING A COMPOSITE MATERIAL PART
The present invention relates to a multiaxial fibre sheet (10) for producing a composite material part (100) for a turbine engine, in particular an aircraft turbine engine, the multiaxial fibre sheet (10) being formed by a stack of multiple layers of fibres (12, 14, 16), each of the layers of fibres comprising unidirectional fibres (12a, 14a, 16a) oriented in different directions from the fibres (12a, 14a, 16a) of the other layers of fibres (12, 14, 16), the layers of fibres (12, 14, 16) being connected to one another by connecting yarns (18), wherein at least one of the layers of fibres (12, 14, 16) is embedded with metal elements (40) configured to dissipate an electric current produced by a lightning strike on the multiaxial fibre sheet (10).
B29C 70/20 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans une seule direction, p. ex. mèches ou autres fibres parallèles
B29C 70/22 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins deux directions formant une structure bidimensionnelle
B29C 70/88 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts caractérisées principalement par des propriétés spécifiques, p. ex. électriquement conductrices ou renforcées localement
A rear assembly for a turbojet engine nacelle includes at least one composite wall separating a cold portion from a hot portion comprising an element to be cooled, the composite wall having first and second skins which extend facing the cold portion and the hot portion respectively, and which are separated from one another by a middle assembly having cells delimited by internal walls. The first skin includes a plurality of through-openings connecting the cold portion and the cells, the internal walls having through-openings connecting the cells to one another, and the second skin having a through-opening which has its mouth facing the element to be cooled.
An air intake module for an aircraft turbomachine extending along a longitudinal axis oriented from upstream to downstream and including an inner wall and an outer wall defining together a vein for circulating an air flow, a plurality of guide vanes of the air flow extending radially in the vein and each comprising an upstream leading edge, at least one stator member fixedly mounted on the inner wall and on the outer wall and extending radially in the vein upstream of the guide vanes, the stator member comprising an infrared wave emitting device configured to emit an infrared beam on the leading edge of at least one of the guide vanes for de-icing it.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
57.
SYSTEM FOR COOLING A REFRIGERANT FOR AN AIRCRAFT COMPRISING A SAFETY HEATING DEVICE AND METHOD FOR USING SUCH A SYSTEM
A system (1) for cooling a refrigerant (R) for an aircraft comprising a plurality of ducts (2) for circulating the refrigerant (R) that are configured to be at least partially in contact with an airflow (A) so as to cool the refrigerant (R) through convection, the cooling system (1) comprising a safety heating device (3) extending internally inside at least one portion of the circulation ducts (2) so as to heat the refrigerant (R), a member (4) for measuring a physical parameter of the refrigerant (R) according to the flow rate of the refrigerant (R) in the circulation ducts (2) and a control member (5) configured to activate the safety heating device (3) when the measured physical parameter is below a predetermined threshold corresponding to a minimum flow rate of the refrigerant (R) in the circulation ducts (2).
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
58.
METHOD AND DEVICE FOR MACHINING AN AERONAUTICAL WORKPIECE
The invention relates to a method (300) and a machining tool for machining a workpiece (1) having a surface (S1, S2) intended to be machined and connected to an edge (B1) of the workpiece (1), the surface (S1, S2) and the edge (B1) extending along a length L1 of the workpiece (1), the method comprising the steps of: a) applying a machining tool (100) to the workpiece (1), the tool (100) comprising at least one reference guide (104, 106a, 106b, 106c) which is brought to bear against the surface (S1, S2) and/or the edge (B1) of the workpiece (1); b) moving the tool (100) along the length L1 so that the rotary member (102) machines the part of the surface according to a predetermined shape profile (PF1, PF2, PF3, PF4), the tool (100) being maintained in bearing contact with the workpiece (1) during this movement.
B23Q 9/02 - Agencements pour le support ou le guidage d'appareils ou de machines portatifs pour le travail du métal pour fixer des machines ou des appareils aux pièces à travailler ou à d'autres pièces de formes particulières, p. ex. à des poutrelles de section particulière
B23C 3/12 - Ébavurage ou finition des arêtes, p. ex. ébarbage des angles soudés
B24B 9/00 - Machines ou dispositifs pour meuler les bords ou les biseaux des pièces ou pour enlever des bavuresAccessoires à cet effet
59.
AIR INLET OF AN AIRCRAFT TURBOMACHINE NACELLE, AND ASSOCIATED METHOD
An air inlet of an aircraft turbomachine nacelle (1) extending along a main axis (X) oriented from front to rear, the air inlet comprising at least one acoustic device (3) comprising an acoustic core (30) on the inner wall (21) between the inner wall (21) and the outer wall (22), the inner wall (21) comprising at least one perforated portion (21P) facing the acoustic core (30) so as to allow the passage of acoustic waves, and at least one vibratory de-icing member (4) positioned in the inner cavity (20) between the acoustic core (30) and the perforated portion (21P), the vibratory de-icing member (4) being in contact with the perforated portion (21P) of the inner wall (21) in order to make it vibrate, and at a distance from the acoustic core (30).
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
60.
METHOD FOR MANUFACTURING AN AERODYNAMIC PANEL FOR AN AIRCRAFT PROPULSION ASSEMBLY
The invention relates to a method for manufacturing an aerodynamic panel (32) for an aircraft propulsion assembly (10), the method comprising the following steps: a) applying at least one reinforcement plate (38, 42, 44) to a first face (34a) of a wall (34); b) rigidly attaching the reinforcement plate (38, 42, 44) to the wall (34, 36) by friction stir welding; c) producing through-holes (50) through the wall (34) and the reinforcement plate (38, 42, 44), these holes (50) being formed through the weld seam (40); and d) fitting screws (52, 54, 56) into the holes (50), these screws (52, 54, 56) comprising countersunk heads (58) that have a thickness (H) greater than the thickness (E1) of the wall (34) and less than the thickness (E3) of the weld seam (40).
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
61.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE DEFLECTING MEMBRANE
The invention relates to a thrust reverser for an aircraft propulsion assembly, comprising a deployable deflecting or obstructing membrane (132) designed to deflect or obstruct at least a portion of the secondary flow escaping from a radial extraction opening when this membrane is in a deployed configuration adopted when the movable structure of the reverser is in a retreated thrust reversal position. According to the invention, in this deployed configuration, the membrane (132) has a generally radially outwardly curved shape defining, at a base (108) of the membrane, an air inlet opening (110) via which air can enter the membrane, the membrane (132) extending between: - a membrane front portion (102) forming a forward flap reaching to the base of the membrane; and - a membrane rear portion (104) forming a rearward flap reaching to the base of the membrane.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
62.
METHOD FOR DEPOSITING A METAL COATING BY THERMAL SPRAYING AND MIXTURE FOR IMPLEMENTING SUCH A METHOD
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventeur(s)
Monerie-Moulin, Francis
Riquet, Audrey
Le Sausse, Nicolas
Abrégé
The invention relates to a method (100) for depositing a metal coating (R) by thermal spraying, which method comprises the following sequential steps: - providing a surface (S) to be coated (110), a tank (2) for a mixture and a metal spraying device (1) connected to the tank, the mixture comprising ellipsoidal metal particles (PMe) and ellipsoidal mineral particles (PMi) having a hardness that is greater than a hardness of the surface and a melting point that is strictly greater than the melting point of the metal particles; - heating the mixture (120) to a temperature below the melting point of the metal particles via neutral gas so as to obtain partially softened and ductile metal particles; - spraying the mixture (130) through the nozzle (20) so as to form a jet of material in the direction of the surface and to form the metal coating on this surface.
C23C 24/08 - Revêtement à partir de poudres inorganiques en utilisant la chaleur ou une pression et la chaleur
B05B 7/20 - Appareillages de pulvérisation pour débiter des liquides ou d'autres matériaux fluides provenant de plusieurs sources, p. ex. un liquide et de l'air, une poudre et un gaz comportant des moyens pour chauffer la matière à projeter sous l'action d'une flamme ou par combustion
C23C 24/10 - Revêtement à partir de poudres inorganiques en utilisant la chaleur ou une pression et la chaleur avec formation d'une phase liquide intermédiaire dans la couche
A method for manufacturing a panel for a nacelle of an aircraft propulsion assembly includes: preparing mold elements each including lateral faces, an upper face, and a lower face; draping a material on a portion of the upper face and/or the lower face and at least one of the lateral faces of each of the mold elements to form at least one fold; and extracting the mold elements such that the at least one fold forms a cellular structure of the panel. The portion of the material on the upper face and/or the lower face forms a peripheral portion of the fold. The portion on the at least one of the lateral faces of each of the mold elements forms a central portion of the fold. The central portion is a portion of transverse partition walls of the panel, which define a plurality of cells.
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
64.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE DEFLECTING MEMBRANE
The invention relates to a thrust reverser for an aircraft propulsion assembly, comprising a deployable deflecting membrane (232) designed to deflect or obstruct at least a portion of the secondary flow escaping from a radial extraction opening when this membrane is in a deployed configuration adopted when the movable structure of the reverser is in a retreated thrust reversal position. According to the invention, the membrane (232) has a generally radially outwardly curved shape extending between a membrane front end secured to a front frame of the support structure (266) and a membrane rear end secured to a rear frame of the support structure.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
65.
DEVICE FOR ATTACHING A HEAT SHIELD TO AN AIRCRAFT PANEL AND ASSOCIATED METHOD
The invention relates to a device (1) for attaching a heat shield (2) to an aircraft panel (3), the device comprising a first attachment element (4) associated with the heat shield (2), a second attachment element (5) associated with the aircraft panel, and a metal wire (6) forming a loop (7). At least one of the attachment elements is provided with means (10, 11) for retaining the loop, the loop being closed by a braking member (12) of the ends (9) of the loop intended for bringing the attachment elements together, the loop abutting one of the attachment elements at its middle portion (8) and the other one of the attachment elements at the braking member (12), respectively. The loop is set apart from the heat shield (2) and the aircraft panel (3), and passes outside the heat shield (2) and the aircraft panel (3).
The invention relates to an acoustic panel (12) with resonators for an aircraft propulsion assembly nacelle, the acoustic panel (12) comprising adjoining acoustic cells (28) which form a cellular core (24), each acoustic cell (28) comprising an enclosure (30) extending along an acoustic propagation axis (L) of the acoustic waves and, inside the enclosure (30), at least one partial obstacle (36, 38) that extends from a wall of the enclosure (30) in a direction transverse to the acoustic propagation axis (L), the at least one obstacle (36, 38) having at least one edge (41a, 41b) rigidly attached to a wall of the enclosure (30) and a free edge (40) that delimits an off-centre internal passage (42) for increasing the length of the path travelled by the acoustic waves through the acoustic cell (28). The at least one partial obstacle (36, 38) further comprises at least one drainage hole (37) adjacent to an edge that is rigidly attached to a wall of the enclosure (30).
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
67.
PROPELLER OF AN AEROPLANE TURBINE ENGINE AND METHOD FOR DE-ICING SAME
The invention relates to a propeller (1) of an aircraft turbine engine, comprising a cone (2) and a plurality of blades (3), the propeller (1) comprising a plurality of electrical de-icing members (4) rigidly connected to a wall (30) of the blades (3), and a control system (6) electrically connected to the electrical de-icing members (4) and comprising at least one electrical switch (7A) having a variable switching duty cycle which is configured, using an input electrical power (Pe), to distribute an output electrical power (Ps) to the electrical de-icing members (4) and to emit a dissipated electrical power (Pd) in the form of heat, at least one electrical switch (7A) of the control system (6) being mounted on an inner face (21) of a wall (20) of the cone (2) so as to transfer the dissipated electrical power (Pd) by thermal conduction into the wall (20) of the cone (2).
A gripping head can be used for applying a patch to a surface to be draped. The gripping head for gripping a patch and applying the patch to a surface to be draped includes a suction chamber delimiting a suction sector and connected to a suction intake and a gripper connected to said suction chamber and comprising a piece of elastically deformable material configured to grip a patch under a gripping effect created in said suction chamber. The gripper includes selectively activatable gripping zones and the gripping head includes means for selectively activating the gripping zones.
Tooling for manufacturing an air deflection cascade for a thrust reverser system of an aircraft nacelle includes a plurality of spars, each spar being connected to at least one adjacent spar by a plurality of deflection vanes. The tooling includes at least one molding bar and at least one molding column of a row of vanes, comprising two opposing lateral faces extending along the longitudinal direction of the tooling, and comprising molding cavities. The tooling includes a fixed structure on which the molding bar and the molding column are mounted. The fixed structure enabling a translational movement, along a transverse direction of the tooling, of the molding bar. The tooling includes a compression device to provide the compression of elements made of a composite material arranged in the tooling and intended to form at least one part of the cascade to be manufactured.
B29C 43/02 - Moulage par pressage, c.-à-d. en appliquant une pression externe pour faire couler la matière à moulerAppareils à cet effet pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 43/36 - Moules pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 70/46 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs"
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
The invention relates to a surface heat exchanger (20), in particular for an aircraft nacelle, comprising a first metal sheet (2) and a second metal sheet (3) that are joined together, and a plurality of distribution channels (4) for a fluid which are arranged between the first metal sheet (2) and the second metal sheet (3), the exchanger further comprising fluid inlet (5) and outlet (6) interfaces. The exchanger further comprises fluid distribution means which define, for each distribution channel (4), a fluid flow section, each of the distribution channels (4) being connected to the inlet (5) and outlet (6) interfaces by such a flow section, the distribution channels (4) being distributed over the entire periphery of the inlet interface (5) and/or of the outlet interface (6).
F28F 3/12 - Éléments construits sous forme d'un panneau creux, p. ex. comportant des canaux
F28F 9/02 - Boîtes de distributionPlaques d'extrémité
F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
71.
THRUST REVERSAL SYSTEM FOR AN AIRCRAFT, AND ASSOCIATED INSTALLATION AND AIRCRAFT
This system (101) comprises a local control module (120) comprising an analogue input port (121) and an analogue wired connection, referred to as control connection (122), between a global control module (104) and the analogue input (121). The local control module (120) is designed to receive, via the control connection (122) and the analogue input (121), movement commands from the global control module (104) in order to control an electric actuator (114) so as to move a cover (112). The local control module (120) furthermore comprises a transmission digital output (152) that is separate from the analogue input (121), the local control module (120) being designed to transmit operating information from the thrust reversal system (101) via the digital output (120).
A method for manufacturing an acoustic panel including a first skin, a second skin and an intermediate structure enclosed between these skins and forming oblique cavities with respect to the latter. The method includes an intermediate polymerization step for fastening the intermediate structure to the first skin in order to increase the compressive strength thereof and in particular to support an automated operation of draping the second skin.
B32B 3/30 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche continue dont le périmètre de la section droite a une allure particulièreProduits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche comportant des cavités ou des vides internes caractérisés par une couche comportant des retraits ou des saillies, p. ex. des gorges, des nervures
B29C 35/02 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation
B29C 65/70 - Assemblage d'éléments préformésAppareils à cet effet par moulage
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29K 63/00 - Utilisation de résines époxy comme matière de moulage
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
B29L 31/38 - Cônes de haut-parleurMembranes acoustiques
B32B 3/26 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche continue dont le périmètre de la section droite a une allure particulièreProduits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche comportant des cavités ou des vides internes
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 15/14 - Produits stratifiés composés essentiellement de métal adjacent à une couche fibreuse ou filamenteuse
B32B 15/20 - Produits stratifiés composés essentiellement de métal comportant de l'aluminium ou du cuivre
An acoustic panel for an aircraft turbomachine has a sandwich structure. The sandwich structure includes a cell structure with a plurality of acoustic cells, a perforated acoustic structure, and a porous acoustic structure attached to the perforated acoustic structure. The perforated acoustic structure is arranged between the cell structure and the porous acoustic structure. The porous acoustic structure is multi-layered and has a first woven textile layer and a second woven textile layer connected to the first layer. The second layer is arranged between the first layer and the perforated acoustic structure.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
74.
ASSEMBLY STRUCTURE AND PROCESS FOR MANUFACTURING A COMPOSITE PART WITH CONTROLLED GEOMETRY
The invention relates to an assembly structure (10) for manufacturing a composite part. The structure comprises:—a skin preform (Pp) and a generally omega-shaped stiffener preform (PT) each having first and second opposing surfaces, the stiffener preform extending along and opposite the first surface of the skin preform. longitudinally and transversely in the form of a stiffener preform cross-section,—a rigid skin tooling (Op) disposed opposite the entire second surface (Sp2) of the skin preform,—a local rigid stiffener tooling (Or1, Or2) extending transversely around the stiffener preform cross-section with a transverse dimension smaller than the transverse dimension of the first surface of the skin preform.
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
(1) Constructions en acier; réservoirs métalliques [structures]; métaux communs et leurs alliages, y compris acier inoxydable; métal antifriction; métal extrudé; métal blanc; tôles métalliques; tôles d'acier; feuilles de métal; pièces métalliques forgées; pièces métalliques embouties; acier; acier inoxydable; acier brut ou mi-ouvré; alliages de métaux communs; aluminium; alliages d'acier.
(2) Machines pour l'usinage des métaux. (1) Traitement des métaux; traitement de métaux à savoir estampage, formage, profilage, embossage, hydroformage; traitement des métaux par hydroformage à base d'explosifs; fourniture de services de formage de métaux par hydroformage à base d'explosif; services de façonnage et de transformation de métaux utilisant la technique de l'hydroformage à base d'explosif pour la production de pièces métalliques conformes à des spécifications particulières; personnalisation et adaptation de pièces métalliques via hydroformage à base d'explosif pour des tiers; traitement thermique des métaux; services d'estampage; emboutissage de métaux; façonnage de composants métalliques; assemblage de matériaux sur commande pour des tiers; services de soudage; usinage de pièces pour des tiers.
(2) Recherche scientifique, technique et industrielle relative aux matériaux et métaux; recherche et développement de nouveaux produits relatifs aux matériaux et métaux; services de conseils techniques, ingénierie et expertise (travaux d'ingénieurs) dans le domaine des matériaux et métaux; essais de machines et de matériaux; services de tests et d'analyse de matériaux; conception de démonstrateurs technologiques; services d'ingénierie en matière de systèmes de formage de métaux; étude de faisabilité de formage de métaux.
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Steel buildings; metal tanks [structures]; common metals and their alloys, including stainless steel; anti-friction metal; extruded metal; white metal; sheet metal; steel sheets; sheets of metal; forged metal parts; pressed metal parts; steel; stainless steel; unwrought or semi-wrought steel; alloys of common metals; aluminum; steel alloys. Machines for metal machining. Treatment of metals; metal treating, namely stamping, forming, profiling, embossing, hydroforming; treatment of metals by hydroforming based on explosives; providing metal forming services by explosive-based hydroforming; metal processing and shaping using the technique of hydroforming based on explosives for production of metal parts complying with particular specifications; customization and adaptation of metal parts via hydroforming based on explosives for third parties; heat treatment of metals; stamping services; deep-drawing of metals; shaping of metal components; custom assembly of materials for third parties; welding services; machining of parts for third parties. Scientific, technical and industrial research relating to materials and metals; research and development of new products relating to materials and metals; technical advisory services, engineering and expertise (engineering work) in the field of materials and metals; machine and material testing; material testing and analysis services; design of technological demonstrators; engineering services relating to metal forming systems; metal forming feasibility study.
77.
Reverser with movable cascades for an aircraft propulsion assembly, comprising a system for limiting the buckling of an actuator of the reverser
A thrust reverser for an aircraft propulsion unit, including a movable system with cascade vanes and an actuator allowing moving a movable system between an advanced direct thrust position and a backward thrust reversal position, the system also including an inter-cascade structure for limiting buckling of the actuator, forming a channel crossed by the actuator and delimited by a cylindrical internal surface extending along a first closed directrix curve, the fixed portion of the actuator including an end equipped with an external ring for limiting buckling of the actuator, the ring having a cylindrical external surface extending along a second closed directrix curve, the first and second closed directrix curves preferably having the same shapes and being concentric while being spaced apart from one another with the same spacing.
F02K 1/76 - Commande ou régulation des inverseurs de poussée
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
78.
ACOUSTIC PANEL FOR AN AIRCRAFT PROPULSION ASSEMBLY AND METHOD FOR PRODUCING SAME
The invention relates to a method for producing an acoustic panel (24') for an aircraft propulsion assembly (10), the panel comprising first and second skins (26, 30) and a cellular layer (28) positioned between the first and second skins (26, 30), the first skin (26) being acoustically permeable and the cellular layer (28) comprising cells (32) that are in fluid communication with perforations (34) in the first skin (26), each of these cells (32) comprising a central well (38) surrounded by peripheral walls (36) of the cell (32), the method comprising a step of producing the cellular layer (28) and a step of assembling the panel (24'), characterised in that the step of producing the cellular layer (28) comprises preparing a sheet (50) and folding this sheet (50) so as to form the cell (32) and its well (38), or so as to form the cells (32) and their wells (38).
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
79.
PROPULSION UNIT COMPRISING PENDULAR BIFURCATION PANELS
A propulsion unit includes a fairing delimiting a flow conduit for a secondary flow. This fairing comprises includes panels, at least one of which is articulated on a mast via connecting members such as clevises.
B64D 29/06 - Fixation des nacelles, carénages ou capotages
F02K 1/32 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour inverser la poussée
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Motors/engines, thrusters, thrust reversers for locomotion
apparatus (except for land vehicles), including aeronautical
vehicles; parts and spare parts for motors/engines and
thrusters for locomotion apparatus (except for land
vehicles), including aeronautical vehicles; parts and spare
parts for thrust reversers for locomotion apparatus (except
for land vehicles), including aeronautical vehicles. Electric and electronic apparatus and instruments, namely,
for measuring, controlling and electric checking of the
opening of motor thrust inverters, potential calculators,
full authority digital engine control (FADEC) calculators,
temperature, pressure, vibration analyses, flight control
calculators; electric, electronic and magnetic sensors for
pressure, speed, displacement, temperature, position,
vibration, electronic cards for processing parameters;
electric connectors; electronic systems and equipment,
whether on board or not, for acquiring and processing data;
electrical and electronic devices and equipment for
maintenance and monitoring (on board aircraft or engines,
fixed on test benches or portable for ground interventions)
for reading and interpreting data from computers and
sensors. Apparatus for locomotion by air, aeronautical vehicles
including aircraft and airplanes; parts and spare parts for
aircraft cabins; nacelles for engines, jet engines and
thrusters for aeronautical vehicles; nacelles for
motors/engines for locomotion apparatus (except for land
vehicles), including aeronautical vehicles; parts and spare
parts of nacelles for motors/engines for locomotion
apparatus (except for land vehicles), including aeronautical
vehicles. Assembly of aeronautical vehicles including airplanes and
aircraft, for third parties; assembly of motors/engines, jet
engines, aeronautical thrust reversers, for third parties;
assembly of components of aeronautical vehicles including
motor/engine nacelles, jet engines, thrusters and thrust
reversers for third parties. Technical, scientific and industrial research in connection
with aeronautical vehicles; research and development of new
products in connection with aeronautical vehicles;
mechanical engineering research in the aeronautical field;
technical advice, research and assistance concerning the
design, certification and modification of aeronautical
vehicles and components thereof, including motor/engine
nacelles, jet engines, thrusters or thrust reversers for
aeronautical vehicles; engineering, professional consulting
and expert reports (services of engineers) in the field of
aeronautics; testing of materials; technical advice and
assistance concerning the manufacture of aeronautical
vehicles and component parts thereof, including motor/engine
nacelles, jet engines, thrusters or thrust reversers,
aeronautical vehicles.
A locking system for an aircraft nacelle is provided. The locking system includes a first portion configured to be mounted on a first part of an aircraft nacelle, and a second portion configured to be mounted on a second part of the aircraft nacelle. The locking system can be configured such that, when it is in the closed position, the first portion and the second portion are held together. The locking system further includes at least one buffer part and a load sensor joined together and configured to compress the load sensor between the buffer part and another part of the locking system when the locking system is in the closed position.
B64D 29/06 - Fixation des nacelles, carénages ou capotages
E05C 5/00 - Dispositifs de fermeture avec pênes se déplaçant autrement que de façon rectiligne uniquement et de façon pivotante ou rotative uniquement
E05C 5/02 - Dispositifs de fermeture avec pênes se déplaçant autrement que de façon rectiligne uniquement et de façon pivotante ou rotative uniquement se déplaçant à la fois selon leur axe et en pivotant autour de leur axe pour bloquer le battant
82.
THRUST REVERSER RING FOR AN AIRCRAFT NACELLE THRUST REVERSER AND AIRCRAFT NACELLE
The invention relates to a thrust reverser ring of an aircraft jet engine extending along a longitudinal axis. The ring comprises thrust reverser modules each extending in a longitudinal direction (D) parallel to the longitudinal axis, the thrust reverser modules being distributed circumferentially about the axis so as to form a ring. One thrust reverser module (10) is arranged between two adjacent thrust reverser modules and is mechanically independent of the latter, the thrust reverser module (10) comprising: - a spar (12) which extends in the longitudinal direction (D) and includes two opposite ends (12c, 12d) spaced apart from each other in this direction, each end being configured to attach the spar to an aircraft nacelle; and - a plurality of transverse blade members (14a, 14b) which are distributed along the spar, extending away from the spar.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
83.
THRUST REVERSER MODULE OF A THRUST REVERSER RING FOR AN AIRCRAFT NACELLE THRUST REVERSER
The invention relates to a thrust reverser module (30) of a thrust reverser ring for an aircraft nacelle thrust reverser, characterised in that the thrust reverser module (30) comprises: - a first spar (42) which extends in a longitudinal direction (D) and carries blade elements (42a1, 42a2, 42a3) each extending transversely relative to the longitudinal direction (D), the transverse blade elements (42a1, 42a2, 42a3) being distributed along the first spar (42); and - a second spar (44) which extends in parallel with the first spar (42) and comprises first and second large opposite faces (44a, 44b), at least one portion of the transverse blade elements (42a1, 42a2, 42a3) of the first spar (42) being connected to the first large face (44a) of the second spar (44) that is arranged opposite, the second large face (44b) of the second spar (44) carrying transverse blade elements (44b1, 44b2, 44b3) which each extend transversely relative to the longitudinal direction of the second spar (44), away from a zone (Z1, Z2, Z3) of the second spar (44) referred to as connection zone of the blade element in question, and in a direction opposite the first large face (44a) of the second spar (44), the transverse blade elements (42a1, 42a2, 42a3) of the at least one portion of the transverse blade elements of the first spar (42) each being connected to the first large face (44a) of the second spar (44), between two successive connection zones (Z1, Z2, Z3) of two successive transverse blade elements (44b1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44), such that the transverse blade elements (42a1, 42a2, 42a3) of the at least one portion of the transverse blade elements of the first spar (42) connected to the second spar and the transverse blade elements (44 b1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44) form a staggered arrangement relative to the second spar.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
84.
Air inlet for an aircraft propulsion unit comprising a member for moving a movable upstream portion and method for using such an air inlet
An air inlet for an aircraft propulsion unit having a movable upstream portion, a stationary downstream portion and at least one member for longitudinally translating the movable upstream portion between a retracted position in which the movable upstream portion is adjacent to the stationary downstream portion, and an extended position in which the movable upstream portion is separated from the stationary downstream portion, the moving member having at least one guiding bar connected to the movable upstream portion and a drive bar having a plurality of teeth, the stationary downstream portion having, for each moving member, a gear wheel configured to co-operate with the teeth in order to form a rack-and-pinion connection and at least one guiding member of the guiding bar.
F01D 17/00 - Régulation ou commande par variation de flux
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
85.
CASCADE FOR A THRUST REVERSER COMPRISING BLADED STAGES CONNECTED BY THEIR CELLULAR STRUCTURES
A cascade (22) of vanes for a cascade thrust reverser (19) for an aircraft propulsion assembly nacelle comprises: a first bladed stage (22A) and a second bladed stage (22B), which are superimposed, each comprising rows of vanes (50A, 50B) and of spars (52A, 52B) which cross over one another so as to form a cellular structure (53A, 53B) for the passage of the air flow; and front (40) and rear (42) end flanges each rigidly connected to all or some of the spars of at least one of the bladed stages. The cellular structures are connected to each other, independently of the front and rear end flanges, by connecting means (66) configured to block relative displacements between the cellular structures. This results in good thrust reversal performance, compatibility with inexpensive manufacturing processes, and a reduction in vibration instability and aerodynamic disturbances.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
86.
THRUST REVERSER FOR AN AIRCRAFT TURBINE ENGINE COMPRISING MEANS FOR DEPLOYING AND RETRACTING, BY MEANS OF A CABLE, A DIAPHRAGM FOR CLOSING THE SECONDARY DUCT
The invention relates to a thrust reverser (30) comprising a movable reverser cowl (33) equipped with a radially inner wall (52) involved in externally defining a secondary duct (21B), the reverser also comprising a diaphragm (58) for closing the secondary duct, as well as means (62) for deploying and retracting the diaphragm. According to the invention, the means (62) comprise: - a cable (64) for driving the diaphragm; and - a member (66) for guiding the first cable, which is mounted on the wall (18). In addition, in the advanced forward thrust position: - a first portion of the cable (64a), which emerges from the guiding member (66), is connected to a first diaphragm end (58a); and - a second portion of the cable (64b), which emerges from the guiding member (66), is connected to the movable reverser cowl (33).
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/76 - Commande ou régulation des inverseurs de poussée
An acoustic assembly including a multicellular acoustic panel having at least one through cavity along a direction X, wherein the acoustic assembly further includes at least one sealing element including a body enclosing one or more acoustic cells, the body being able to be inserted into the cavity and extending along the direction X between a first face and a second face, the sealing element further including a seal on the second face of the body able to ensure the sealing with the acoustic panel.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
This device (1) for counting a number of mechanical cycles produced by a cyclically moving part comprises a module (4) for storing the number of mechanical cycles produced by the mobile part, a module (3) for detecting a mechanical cycle produced by the mobile part capable of incrementing the number stored in the storage module (4) and a module for transmitting, upon request, (5) the stored number able to recover the number stored in the storage module (4), the detection module (3) comprising a piezoelectric generator (6) configured to determine an embodiment of a mechanical cycle by the mobile part and the on-demand transmission module (5) comprising an RFID tag (12) provided with an antenna (13).
G01H 11/08 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores par détection des changements dans les propriétés électriques ou magnétiques par des moyens électriques utilisant des dispositifs piézo-électriques
G07C 3/04 - Enregistrement ou indication du temps de fonctionnement ou d'arrêt seulement utilisant des moyens de comptage ou compteurs à horloge
B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
89.
DEVICE FOR DETECTING THE POSITION OF A MOBILE PART, AND ASSOCIATED METHOD AND AIRCRAFT
This device (2) for detecting the position of a mobile part (1) able to move between a first extreme position, a second extreme position and at least one intermediate position, comprises a fixed antenna (3) and a plurality of radio-frequency identification tags (4, 4a, 4b, 4c) arranged along the path of the mobile part (1) between said extreme and intermediate positions, the device (2) further comprising a mechanical contactor (5) configured to establish an electrical connection between the antenna (3) and a unique combination of at least one radio-frequency identification tag (4, 4a, 4b, 4c) for each position of the mobile part (1).
G01D 5/252 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques sélectionnant un ou plusieurs conducteurs ou circuits parmi un certain nombre de conducteurs ou circuits, p. ex. en fermant des contacts une combinaison de conducteurs ou circuits
H01Q 1/22 - SupportsMoyens de montage par association structurale avec d'autres équipements ou objets
G06K 19/07 - Supports d'enregistrement avec des marques conductrices, des circuits imprimés ou des éléments de circuit à semi-conducteurs, p. ex. cartes d'identité ou cartes de crédit avec des puces à circuit intégré
G06K 19/077 - Détails de structure, p. ex. montage de circuits dans le support
90.
Thrust reverser with cascades of mobile vanes, comprising a rear structure supporting the cascades of vanes and incorporating an acoustic function
A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
The invention relates to a thrust reverser assembly for a turbojet engine, comprising a stationary structure having a main axis; a shroud, movable and capable of translational movement along the main axis between an attached position in which the shroud is attached to the stationary structure, and a spaced position in which the shroud is spaced from the stationary structure; at least one latch capable of holding the stationary structure and the shroud in the attached position; at least one actuator mounted between the stationary structure and the shroud and configured to move the shroud along the main axis between the attached position and the spaced position; and a seal configured to provide a seal between the stationary structure and the shroud in the attached position, wherein the seal has a tapered cross section.
F02K 1/76 - Commande ou régulation des inverseurs de poussée
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
92.
ACOUSTICALLY-TREATED AIR EJECTION NOZZLE FOR A NACELLE
An air ejection nozzle for a nacelle includes an outer aerodynamic line and an inner aerodynamic line meeting at a trailing edge. The air ejection nozzle includes at discrete positions at least one area of larger thickness that is compensated by at least one fairing to connect the aerodynamic lines to form the trailing edge. The fairing includes an outer wall and an inner wall delimiting a cavity therebetween. The inner wall provides for the continuity of the inner aerodynamic line, and the outer wall is solid and the inner wall is pierced so that the at least one fairing forms an acoustic attenuation structure.
F02K 1/34 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour atténuer le bruit
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
93.
METHOD AND SYSTEM FOR CONTROLLING THE APPLICATION OF A PATCH
A method for controlling the application of a patch can include the following steps:
positioning a patch on a surface to be covered by means of a gripper and with or without partial overlapping with adjacent patches;
acquiring by means of an optical control means at least one image of the positioned patch;
detecting defects in the positioning of the patch by identifying differences in the thickness of the patch on the surface to be covered based on the at least one image of the positioned patch; and
mapping the defects in the positioning of the patch.
The invention relates to a jet deflection module (26) for a thrust reverser (10) of an aircraft turbine engine, this module (26) extending in a surface (P) and including: - longitudinal members (32) which are spaced apart from one another and parallel to one another; - at least one deflection element which extends between the longitudinal members (32) and which is connected to these longitudinal members (32); and - two attachment profiles, front (36) and rear (38), respectively, which are connected to the longitudinal members (32), these two profiles (36, 38) forming, with two of these longitudinal members (32), a peripheral contour of the module, characterised in that a first of the attachment profiles (36, 38) comprises a plurality of hooks (70) at a distance from one another, each of these hooks (70) comprising at least one opening (72) oriented perpendicularly to the surface (P) and additionally a bearing surface (74) parallel to this surface (P).
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
95.
JET DEFLECTION MODULE FOR A THRUST REVERSER OF AN AIRCRAFT TURBINE ENGINE
The invention relates to a jet deflection module (26) for a thrust reverser (10) of an aircraft turbine engine, this module (26) extending in a surface (P) and comprising: - longitudinal members (32) which are spaced apart from one another and parallel to one another; - at least one deflection member (34) which extends between the longitudinal members (32) and which is connected to these longitudinal members (32); - two, respectively front (36) and rear (38), attachment profiles which are connected to the longitudinal members (32) and which form, together with two of these longitudinal members (32), a peripheral contour of the module (26), a first of the attachment profiles (36, 38) comprising at least two clevis joints (90) which are parallel to one another and to the longitudinal members (32) and which each comprise a hole (92), the holes (92) of the clevis joints (90) being aligned and defining a pivoting axis (A) of the module (26), characterised in that the clevis joints (90) extend in the continuation of the longitudinal members (32).
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Motors and engines, thrusters, and thrust reversers for aeronautical vehicles, namely turbines, pumps, reactors, nacelles, thrust reversers, engine air intake, fan casing, exhaust cones, excluding land vehicles; parts and spare parts for motors, engines, and thrusters for aeronautical vehicles, excluding land vehicles; parts and spare parts for thrust reversers for motors, engines, and thrusters for aeronautical vehicles, excluding land vehicles; All of the aforementioned goods being used outside of the semiconductor field. Assembly line for aeronautical vehicles including airplanes and aircraft, for third parties; assembly line for motors and engines, jet engines, and aeronautical thrust reversers, for third parties; assembly line for components of aeronautical vehicles including motor and engine nacelles, jet engines, thrusters and thrust reversers for third parties. Electric and electronic apparatus and instruments, namely, sensors, scanners, chemical fumes detectors, radiographic apparatus, for measuring, controlling and electric checking of the opening of motor thrust inverters, potential calculators, full authority digital engine control (FADEC) calculators, temperature, pressure, vibration analyses, and flight control calculators; electric, electronic and magnetic sensors for monitoring, measuring pressure, speed, displacement, temperature, position, vibration; electronic cards for processing parameters; electric connectors; electronic systems and equipment, whether on board or not, for acquiring and processing data; electrical and electronic devices and equipment for maintenance and monitoring (on board aircraft or engines, fixed on test benches or portable for ground interventions) for reading and interpreting data from computers and sensors; All of the aforementioned goods being used outside of the semiconductor field. Apparatus for locomotion by air, namely, aeronautical vehicles, aircraft, and airplanes; parts and spare parts for aircraft cabins; nacelles comprised of an inlet cowl, fan cowls, pylon/strut, exhaust nozzle, and exhaust cone for engines, jet engines and thrusters for aeronautical vehicles; nacelles for motors and engines for aeronautical vehicles, excluding land vehicles; parts and spare parts of nacelles, namely friction, damping, clutch and braking devices for aerial vehicles, namely, brakes, shock absorbers and clutches for motors and engines for aeronautical vehicles, excluding land vehicles. Technical, scientific and industrial research in the field of aeronautical vehicles for others, namely on motors and engines, thrusters, and thrust reversers; research and development of new products in the field of aeronautical vehicles for others, namely on motors and engines, thrusters, and thrust reversers; mechanical engineering research in the aeronautical field for others namely on motors and engines, thrusters, and thrust reversers; technical advice, research and assistance concerning the design, certification and modification of aeronautical vehicles and components thereof, including motor and engine nacelles, jet engines, thrusters and thrust reversers for aeronautical vehicles; engineering, professional consulting and engineering services, namely, creating expert reports in the field of aeronautics; testing of materials; technical advice and assistance in the field of manufacturing of aeronautical vehicles and component parts thereof, namely, motor and engine nacelles, jet engines, thrusters and thrust reversers for aeronautical vehicles.
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
(1) Moteurs, propulseurs, inverseurs de poussées pour appareils de locomotion (à l'exception de ceux pour véhicules terrestres), y compris véhicules aéronautiques; parties et pièces détachées pour moteurs et pour propulseurs pour appareils de locomotion (à l'exception de ceux pour véhicules terrestres), y compris véhicules aéronautiques; parties et pièces détachées pour inverseurs de poussée pour appareils de locomotion (à l'exception de ceux pour véhicules terrestres), y compris véhicules aéronautiques.
(2) Appareils et instruments électriques et électroniques à savoir de mesure, de commande et de contrôle électrique d'ouverture d'inverseur de poussée de moteur, calculateurs de potentiel, calculateurs de régulation numérique de vitesses et de débits de carburant (FADEC), calculateurs de températures, de pressions, d'analyses vibratoires, de commandes de vol; capteurs électriques, électroniques et magnétiques de pressions, de vitesses, de déplacements, de températures, de positions, de vibrations, cartes électroniques de traitements de paramètres; connecteurs électriques; systèmes et équipements électroniques, embarqués ou non, d'acquisition et de traitement de données; matériels et équipements électriques et électroniques de maintenance et de contrôle (embarqués sur avions ou moteurs, fixes sur bancs d'essais ou portables pour interventions au sol) permettant de lire et d'interpréter les données des calculateurs et des capteurs.
(3) Appareils de locomotion par air, véhicules aéronautiques y compris aéronefs et avions; parties et pièces détachées de carlingues de véhicules aéronautiques; nacelles pour moteurs, réacteurs et propulseurs de véhicules aéronautiques; nacelles pour moteurs et pour propulseurs pour appareils de locomotion (à l'exception de ceux pour véhicules terrestres), y compris véhicules aéronautiques; parties et pièces détachées de nacelles pour moteurs et pour propulseurs pour appareils de locomotion (à l'exception de ceux pour véhicules terrestres), y compris véhicules aéronautiques. (1) Assemblage de véhicules aéronautiques y compris d'avions et d'aéronefs, pour des tiers; assemblage de moteurs, de réacteurs, d'inverseurs de poussée aéronautiques, pour des tiers; assemblage de parties constitutives de véhicules aéronautiques y compris de nacelles de moteurs, de réacteurs, de propulseurs et d'inverseurs de poussée pour des tiers.
(2) Recherche scientifique, technique et industrielle relative aux véhicules aéronautiques; recherche et développement de nouveaux produits relatifs aux véhicules aéronautiques; recherche en mécanique dans le domaine aéronautique; conseils, recherche et assistance techniques concernant la conception, la certification et la modification de véhicules aéronautiques et de leurs parties constitutives, y compris de nacelles de moteurs, de réacteurs, de propulseurs ou d'inverseurs de poussée, de véhicules aéronautiques; consultations professionnelles, ingénierie et expertise (travaux d'ingénieurs) dans le domaine aéronautique; essais de matériaux; conseils et assistance techniques concernant la fabrication de véhicules aéronautiques et de leurs parties constitutives, y compris de nacelles de moteurs, de réacteurs, de propulseurs ou d'inverseurs de poussée, de véhicules aéronautiques.
98.
AIRCRAFT PROPULSION ASSEMBLY COMPRISING AN ACTUATOR CONNECTED TO A STRUCTURAL ARM SUCH AS AN OUTLET GUIDE VANE
A propulsion assembly including an actuator connected to an outer casing of a turbomachine by a connecting structure. The connecting structure is fastened in line with a structural arm connecting the outer casing to a hub of the turbomachine, with a common fastening device, with the result that the arm can withstand loading forces of the actuator while relieving the outer casing.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/76 - Commande ou régulation des inverseurs de poussée
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Motors/engines, thrusters, thrust reversers for locomotion
apparatus (except for land vehicles), including aeronautical
vehicles; parts and spare parts for motors/engines and
thrusters for locomotion apparatus (except for land
vehicles), including aeronautical vehicles; parts and spare
parts for thrust reversers for locomotion apparatus (except
for land vehicles), including aeronautical vehicles. Electric and electronic apparatus and instruments, namely,
for measuring, controlling and electric checking of the
opening of motor thrust inverters, potential calculators,
full authority digital engine control (FADEC) calculators,
temperature, pressure, vibration analyses, flight control
calculators; electric, electronic and magnetic sensors for
pressure, speed, displacement, temperature, position,
vibration, electronic cards for processing parameters;
electric connectors; electronic systems and equipment,
whether on board or not, for acquiring and processing data;
electrical and electronic devices and equipment for
maintenance and monitoring (on board aircraft or engines,
fixed on test benches or portable for ground interventions)
for reading and interpreting data from computers and
sensors. Apparatus for locomotion by air, aeronautical vehicles
including aircraft and airplanes; parts and spare parts for
aircraft cabins; nacelles for engines, jet engines and
thrusters for aeronautical vehicles; nacelles for
motors/engines for locomotion apparatus (except for land
vehicles), including aeronautical vehicles; parts and spare
parts of nacelles for motors/engines for locomotion
apparatus (except for land vehicles), including aeronautical
vehicles. Assembly of aeronautical vehicles including airplanes and
aircraft, for third parties; assembly of motors/engines, jet
engines, aeronautical thrust reversers, for third parties;
assembly of components of aeronautical vehicles including
motor/engine nacelles, jet engines, thrusters and thrust
reversers for third parties. Technical, scientific and industrial research in connection
with aeronautical vehicles; research and development of new
products in connection with aeronautical vehicles;
mechanical engineering research in the aeronautical field;
technical advice, research and assistance concerning the
design, certification and modification of aeronautical
vehicles and components thereof, including motor/engine
nacelles, jet engines, thrusters or thrust reversers for
aeronautical vehicles; engineering, professional consulting
and expert reports (services of engineers) in the field of
aeronautics; testing of materials; technical advice and
assistance concerning the manufacture of aeronautical
vehicles and component parts thereof, including motor/engine
nacelles, jet engines, thrusters or thrust reversers,
aeronautical vehicles.
100.
Reinforced acoustic treatment panel for an aircraft propulsion unit
An acoustic treatment panel intended to be disposed on at least one wall of an aircraft propulsion unit in contact with a fluidic flow, the panel including a first, acoustically reflective skin, a second, acoustically porous skin intended to be in contact with the fluidic flow, and a honeycomb structure extending between the first skin and the second skin and having a plurality of cavities. The panel includes at least one acoustically transparent reinforcing wall passing through a plurality of cavities of the honeycomb structure and extending from the second skin to the first skin, forming a non-orthogonal angle with the first and second skins.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
G10K 11/168 - Sélection de matériaux de plusieurs couches de matériaux différents, p. ex. sandwiches
