The invention relates to a plate heat exchanger (1) configured for a heat exchange between a first fluid flowing in a first pass and a second fluid flowing in a second pass, the fluids flowing between two external plates (2), comprising a plate exchanger block comprising a plurality of internal plates (12, 14) arranged substantially in parallel with each other, said internal plates being arranged substantially in parallel with the external plates (2),
The invention relates to a plate heat exchanger (1) configured for a heat exchange between a first fluid flowing in a first pass and a second fluid flowing in a second pass, the fluids flowing between two external plates (2), comprising a plate exchanger block comprising a plurality of internal plates (12, 14) arranged substantially in parallel with each other, said internal plates being arranged substantially in parallel with the external plates (2),
characterized in that it comprises at least one lateral encapsulation plate (20) extending substantially orthogonally to said internal plates, each lateral encapsulation plate being fixed in contact with said external plates (2) so as to laterally close said second pass.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
The present disclosure relates to a computer-implemented method for transmitting data, in particular in a flight control, comprising the steps of:
transmitting a synchronisation signal via a first processing unit;
receiving the synchronisation signal by a second and/or a third processing unit, at a receiving timepoint in each case;
transmitting first data from the third processing unit to the second processing unit, wherein the transmission of the first data takes place at a first transmission timepoint which depends on the respective receiving timepoint of the reception of the synchronisation signal by the second and/or third processing unit;
transmitting the first and/or second data from the second processing unit to the first processing unit, wherein the transmission takes place at a second transmission timepoint which depends on the respective receiving timepoint of the reception of the synchronisation signal by the second and/or third processing unit.
The invention relates to a heat-exchange device comprising:
an exchanger block (12) disposed in a flow enclosure defined by two external plates,
said exchanger block comprising a first internal layer and a last internal layer allowing the flow of the first heat-transfer fluid, said exchanger block comprising a plurality of internal plates (13, 14, 15, 16) disposed substantially in parallel with each other between two ends of said exchanger block,
characterized in that each first internal layer and each last internal layer comprises at least one flow limiting device (20) configured to be able to impede, at least in part, the flow of said first stream of fluid in said internal layer.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
4.
HEAT EXCHANGE DEVICE COMPRISING AT LEAST ONE MANIFOLD, AND AIR CONDITIONING SYSTEM AND VEHICLE
The invention relates to a heat exchange device comprising: a heat exchange matrix (50) accommodated in a circulation enclosure and formed of a plurality of heat exchange pipes, each pipe comprising at least one duct extending mainly in a longitudinal direction, each duct at least partially defining a flow channel for a second heat transfer fluid, at least one manifold (20) comprising at least one duct portion (22, 23, 24) extending mainly in a plane orthogonal to the longitudinal direction, the manifold comprising a plurality of ports (30), at least one fluid distribution header (40) configured to allow a second heat transfer fluid to flow between at least one port of the manifold and at least one duct, each port of the manifold opening into a distribution header. The invention relates to an air conditioning system and to an aircraft comprising such a heat exchange device.
The present invention relates to a system for adjusting a valve, in particular a servo valve, wherein the valve comprises a nozzle and a flow divider, with a positioning unit which is configured to position the nozzle relative to the flow divider, a measuring unit which is configured to determine a pressure and/or flow rate in at least one line branching off from the flow divider, and a control unit which is configured to control the positioning unit to position the nozzle relative to the flow divider based upon a pressure and/or flow rate determined by the measuring unit, and a control unit which is configured to control the positioning unit based upon a pressure and/or flow rate determined by the measuring unit in order to position the nozzle relative to the flow divider in such a way that a desired pressure and/or flow rate results in the at least one line.
The present invention relates to a method for adjusting a valve, in particular a servo valve comprising a first stage and a second stage, comprising the steps of: only partially limiting a range of movement of a valve spool which is configured to open and/or close at least one port of the valve so that the spool is movable; applying the valve with a fluid, and changing a position of a nozzle of the valve relative to a jet divider until the at least one port is completely closed by the movable spool. A method according to the invention is preferably used in the manufacture of an aircraft, preferably airplanes.
The present disclosure relates to a system for monitoring and/or detecting an operational state of a movable component of an aircraft, wherein the system has a movable component and a monitoring device, wherein the system also has a combination sensor connected to the monitoring device, which is designed and arranged to detect a kinematic and/or kinetic state of the component, wherein the monitoring device is designed to monitor and/or detect an operational state of the component.
The invention relates to an aircraft pylon comprising a cooling exchanger (10) with counterflow of a flow of hot primary air (22) by a flow of cold secondary air (24) flowing oppositely to each other in a longitudinal direction (L), characterized in that it comprises two bundles (10a, 10b) juxtaposed on both sides of a central axis (12) and each comprising a plurality of parallel longitudinal plates (15) forming a hot pass and a cold pass of the bundle, and in that one of the hot or cold passes of each bundle is supplied by a central inlet (14a) common to the two bundles (10a, 10b) and one of the hot or cold passes of each bundle opens into a central outlet (16) common to the two bundles, said inlets (14b, 14c) and outlets (16b, 16c) of the conjugate passes, referred to as side inlets and outlets, being separate and diverging laterally from said central axis (12).
B64D 27/40 - Arrangements for mounting power plants in aircraft
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
9.
METHOD AND APPARATUS FOR CONDUCTING HEALTH MONITORING DURING GROUND OPERATION
A health monitoring method for checking a functionality of a flight control surface driving apparatus using a load sensor for sensing a load imposed on a control surface drive device by: comparing a load sensor output signal of the load sensor with a first while operating the control surface drive device to move the at least one control surface to a predetermined extended position; or, comparing a load sensor output signal of the load sensor with a second threshold while operating the control surface drive device to move the control surface from an extended position to a retracted position; or both. Also a flight control surface drive apparatus, a flight control system and an aircraft.
The invention relates to a method for manufacturing a heat exchanger comprising at least one tube (12) for circulating a fluid and configured to allow heat exchange between the fluid circulating through each tube (12) and a profile surrounding each tube, characterised in that it comprises a step of cold gas dynamic spraying of metal powder onto each tube (12) arranged in a first mould so as to form a first profile portion (14a), and a step of cold gas dynamic spraying of metal powder onto each tube (12) arranged in a second mould (16b) so as to form a second profile portion (14b).
A health monitoring method for checking a functionality of a flight control surface driving apparatus using a load sensor for sensing a load imposed on a control surface drive device by: blocking movement of the transmission device with a brake device, commanding the control surface drive device to apply a load on the blocked transmission device, and determining whether a load sensor output signal of the load sensor is within a predetermined range. Also, a flight control surface drive apparatus, a flight control system and an aircraft.
The invention relates to a fluid system of an aircraft comprising at least one flow conduit for a fluid, at least one electric valve (30, 40, 50) for regulating the flow of fluid in said fluid conduit by movement of a regulating member in said fluid conduit, a central computer (20) configured to be able to issue control instructions to each electric regulating valve (30, 40, 50) depending on the in-flight conditions of said aircraft, and an electric circuit (60) for powering said computer and each electric regulating valve, characterized in that at least one electric regulating valve, referred to as smart valve, is equipped with an integrated actuator connected to the central computer and/or to another smart valve of the fluid system by at least one multiplexed data communications bus (22, 24, 42, 44).
F16K 31/04 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a motor
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
F16K 37/00 - Special means in or on valves or other cut-off apparatus for indicating or recording operation thereof, or for enabling an alarm to be given
13.
DEVICE FOR SUPPLYING A PLURALITY OF CATHODES OF A FUEL SYSTEM
The invention relates to a supply device for compressed air to a plurality of cathodes (100a-100d) of a fuel cell system, characterized in that it comprises a motorized compressor (12) configured to provide a source of compressed air to all of the cathodes (100a-100d), a group of ducts configured to conduct the compressed air to each cathode (100a-100d), for each cathode (100a-100d), a proportioning valve (20a-20d) upstream or downstream of said cathode (100a-100d) which is configured to regulate the flow rate of compressed air passing through said cathode (100a-100d), anti-pumping protection means (30, 32) configured to allow the flow of a minimum flow rate of compressed air leaving the compressor (12), and a control device (24) configured to control the speed of the compressor (12) and the opening or closing of each proportioning valve (20a-20d) and/or the operation of the anti-pumping protection means (30, 32).
The present disclosure relates to a system for detecting the position and/or the operating state of a movable component of an aircraft, wherein the system has one movable component, two actuators, two motion sensors, one asymmetry sensor, one drive train, and one monitoring device; wherein the component can be actuated by the at least two mutually offset actuators; wherein at least one motion sensor is provided for one respective actuator; wherein the motion sensor can monitor a mechanical movement of the drive train; wherein the monitoring device is connected to the motion sensors and to the asymmetry sensor, and wherein the system is configured such that an initialization of the monitoring device and/or of the motion sensors and/or of the asymmetry sensor can take place after a booting of the system and/or when the component has adopted a fully retracted and/or a fully extended position.
The present invention relates to a system for detecting the position and/or the operating state of a movable component of an aircraft, wherein the system has one movable component, two actuators, two motion sensors, one asymmetry sensor, one drive train, and one monitoring device; wherein the component can be actuated by the at least two mutually offset actuators; wherein at least one motion sensor is provided for one respective actuator; wherein the motion sensor can monitor a mechanical movement of the drive train; wherein the monitoring device is connected to the motion sensors and to the asymmetry sensor, and wherein the system is configured such that an initialization of the monitoring device and/or of the motion sensors and/or of the asymmetry sensor can take place after a booting of the system and/or when the component has adopted a fully retracted and/or a fully extended position.
The present disclosure relates to a blocking unit for a component of an aircraft movable by at least one movement means, wherein the component can assume at least one blocking position and at least one movement position, wherein the blocking unit comprises blocking means, wherein the blocking means are arranged and designed to block a movement of the component when a blocking condition is fulfilled, wherein the blocking unit has locking means, wherein the locking means are arranged and designed such that the blocking means are prevented from blocking the movement of the component when the component is in a movement position, and wherein the locking means are arranged and designed such that the blocking means are not prevented from blocking the movement of the component when the component is in a blocking position.
The invention relates to a method for installing coil groups in an electric machine (100), each coil group (104, 204) comprising at least one coil, each coil being composed of a plurality of turns of conductors, characterized in that it comprises, for each coil group (104, 204), the following installation steps applied to each coil group before being applied to the following coil group: a step of inserting a first coil group into at least two free or partially occupied slots (106) of the electric machine (100), the coil portions arranged outside the slots forming the coil heads, a definitive shaping step by compacting the heads of the coils of said coil group into a predetermined shape, by a preconfigured apparatus.
H02K 15/00 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
H02K 3/38 - Windings characterised by the shape, form or construction of the insulation around winding heads, equalising connectors, or connections thereto
H02K 15/10 - Applying solid insulation to windings, stators or rotors, e.g. applying insulating tapes
18.
HEAT EXCHANGER WITH A CLOSING BAR OPTIMIZED FOR PROTECTION AGAINST ICING
Heat exchanger with plates, which is configured for a heat exchange between a hot fluid and a cold fluid, comprising at least one core band (130a, 130b) arranged in order to maintain the sealing tightness, a plurality of closing bars (138) defining, with the closing plates, flow channels, characterized in that the core band (130a) arranged at a cold pass inlet and at a hot pass inlet comprises an inlet (132) for supplying hot air, and in that at least one closing bar (138) arranged in the lengthwise direction of the inlet of the cold pass comprises an inlet for said hot air and a flow circuit for said hot air in a U shape and comprising two sections, each extending over the whole length of the closing bar, a hot air outlet for expelling the hot air in the hot pass, and an intermediate section forming the base of the U.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
The present disclosure relates to a valve, preferably a continuous valve or a proportional valve, wherein the valve comprises means configured to control and/or regulate a pressure and/or flow of a fluid, wherein the means are further configured to effect at least one further function or to participate in the function.
F15B 13/04 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
F16K 27/04 - Construction of housingsUse of materials therefor of sliding valves
F16K 11/07 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with linearly sliding closure members with cylindrical slides
20.
METHOD FOR LOCATING AN AIR LEAK IN A NETWORK FOR SUPPLYING PRESSURIZED AIR, ASSOCIATED COMPUTER PROGRAM PRODUCT AND SYSTEM
Described herein is the location of an air leak in a network for supplying pressurized air that includes one or more components and at least one leak detection loop including one or more sensing elements. The location includes receiving information representative of detection of the leak by a sensing element of the detection loop, receiving a 3D model of at least part of the network for supplying pressurized air, interrogating a database associating a leak site of a component with each location on the detection loop, determining a precise location of the leak on the network for supplying pressurized air, mapping the precise location relative to a component, and instructing display of the 3D model corresponding to the component of the supply network and of the precise location.
G01M 3/04 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
G06F 30/18 - Network design, e.g. design based on topological or interconnect aspects of utility systems, piping, heating ventilation air conditioning [HVAC] or cabling
21.
METHOD FOR LOCALIZATION OF AN AIR LEAK IN A PRESSURIZED AIR SUPPLY NETWORK, ASSOCIATED COMPUTER PROGRAM PRODUCT AND SYSTEM
L'invention concerne un procédé de localisation d'une fuite d'air dans un réseau d'alimentation en air pressurisé comprenant une pluralité de composants et au moins une boucle de détection de fuite comprenant une pluralité d'éléments sensibles, comprenant une étape de réception d'une information représentative d'une détection de la fuite par un élément sensible de ladite boucle de détection, une étape de réception d'un modèle 3D d'au moins une partie du réseau d'alimentation en air pressurisé, une étape d'interrogation d'une base de données associant un emplacement de fuite d'un composant à chaque localisation sur la boucle de détection, une étape de détermination d'une localisation précise de ladite fuite sur le réseau d'alimentation en air pressurisé, une étape de mise en correspondance de ladite localisation précise relativement à un composant, une étape d'instructions d'affichage du modèle 3D correspondant audit composant du réseau d'alimentation et de ladite localisation précise.
The present disclosure relates to a valve, preferably a continuous valve comprising a spool and a spool sleeve, wherein the spool comprises a control surface and the spool sleeve comprises an opening, wherein the valve is configured in such a way that the control surface can cover the opening, wherein the spool can be positioned such that the control surface at least partially does not cover the opening, wherein the spool sleeve comprises a further opening, wherein the control surface can cover the further opening, wherein the spool can be positioned such that the control surface at least partially does not cover each of the opening and the further opening.
F15B 13/04 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
F16K 11/07 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with linearly sliding closure members with cylindrical slides
23.
HEAT EXCHANGER WITH A FLUID FLOW TUBE AND PROTECTION AGAINST MICROMETEORITES
A heat exchanger includes a fluid flow tube configured to allow an exchange of heat between the fluid flowing in the tube and an enclosure surrounding the tube. The enclosure is formed from two profiled bars configured to surround the tube over at least one part of its length. Each of the bars includes a recess adapted to receive the tube, and a joint surface configured to form a joint with the other profiled bar. The joint surfaces of the profiled bars form a gap therebetween. As well, the joint surfaces of the profiled bars are arranged in different planes such that the gap forms at least one baffle on each side of the tube.
B23K 1/00 - Soldering, e.g. brazing, or unsoldering
F28F 1/20 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending longitudinally the means being attachable to the element
F28F 21/08 - Constructions of heat-exchange apparatus characterised by the selection of particular materials of metal
24.
SYSTEM AND METHOD FOR COOLING A FUEL CELL ASSEMBLY
The invention relates to a system for cooling a fuel cell assembly (10) of a transport vehicle, such as an aircraft, comprising: a cooling fluid circulation loop (20); a cooling heat exchanger (24) configured to be able to provide heat exchanges between said loop (20) and a channel (25) for circulating cooling air (26); a variable-speed pump (21) for supplying said cooling loop with cooling fluid as a function of a measurement representative of the cooling need of said fuel cell assembly; for each fuel cell (10a, 10b, 10c) of said cell assembly, a 3-way valve (12a, 12b, 12c) for regulating the flow rate of cooling fluid supplying this cell as a function of a measurement representative of the cooling need of this cell.
H01M 8/249 - Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
25.
MODULE FOR SUPPLYING PRESSURIZED FRESH AIR TO AN AIR-CONDITIONING PACK OF AN AIRCRAFT CABIN, AIR-CONDITIONING SYSTEM EQUIPPED WITH SUCH A MODULE, AND CORRESPONDING METHOD
The invention relates to an air-conditioning system for an aircraft cabin (5) comprising: an engine air bleed device (10); an air-conditioning pack (20) comprising a pack air inlet (21) connected to said engine bleed device (10), and a pack air outlet (22) connected to said cabin (5); an auxiliary module (50) for supplying pressurized air comprising an auxiliary turbomachine (51), comprising a compressor (52) supplied with external fresh air and a turbine suitable to be able to be supplied with air coming from the engine bleed device; and a control unit configured to activate either a standard mode in which the pack air inlet is supplied with the pressurized air coming from the engine bleed device (10), or a fresh air mode in which said pack air inlet (21) is supplied with the pressurized air coming from the auxiliary module (50).
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
26.
System for providing protection from icing using a fuel cell
b), and two liquid-liquid heat exchangers (116, 216) in which the cooling liquids form a hot pass and the icing protection liquids form a cold pass to reheat the icing protection liquid by the heat from the cooling liquids.
The invention relates to a profiled part (12) for a heat exchanger, configured to have at least one fluid flow tube (14) passing through it, comprising, for each flow tube (14), a hollow cylinder (18) comprising an inner surface configured to receive said flow tube (14), the cylinder (18) having an inner diameter which is substantially equal to the outer diameter of said flow tube (14). The profiled part (12) is characterized in that the profiled part comprises a slit (16) extending over the whole length of the cylinder (18) and configured to permit, by application of at least one mechanical force to the profiled part, a modification in the inner diameter of the cylinder (18) in order respectively to permit the insertion of the tube into the cylinder (18) or the clamping of the tube (14) by the inner surface of the cylinder (18). The invention also relates to a heat exchanger (10) comprising such a profiled part (12) and a flow tube (14).
F28F 1/20 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending longitudinally the means being attachable to the element
28.
VIBRATION ABSORBING DEVICE WITH A WEIGHTED MEMBRANE ANO FLUID DISPLACEMENT
INSTITUT SUPÉRIEUR DE L'AÉRONAUTIQUE ET DE L'ESPACE (France)
Inventor
Roncen, Thomas
Manet, Vincent
Michon, Guilhem
Abstract
Vibration absorbing device comprising a housing (12), a membrane (14) enclosed in the housing (12) and thus forming two chambers (18a, 18b) in the housing (12), said chambers (18a, 18b) being filled with a fluid, at least one weight (16), arranged on the membrane (14) in order that a movement of the weight (16) causes a movement of the membrane (14), and at least one duct (24) arranged to permit the fluid to flow between the two chambers (18a, 18b) if the membrane (14) and the weight (16) move.
A heat-exchange device includes a flow enclosure defined by two external plates, a first inlet and a first outlet for a first heat-transfer fluid, a second inlet and a second outlet for a second heat-transfer fluid, and an exchanger block with plates disposed in the flow enclosure so as to be in fluid communication with the inlets and outlets in order to permit the flow of the first fluid and of the second fluid into and through this exchanger block and the transfer of calories therebetween. Each external plate has at least one hollow. An air-conditioning system may include such device and an aircraft, in turn, can include such air-conditioning system.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F24F 13/30 - Arrangement or mounting of heat-exchangers
F28F 3/04 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
30.
Control electronics, electromechanical actuator, aircraft and method for damping the movement of an electromechanical actuator
The present invention relates to control electronics, preferably for an electromechanical actuator, preferably for use in a primary flight control system of an aircraft, wherein the control electronics can connect or connects an electric motor, preferably of the electromechanical actuator, to an electrical or electronic load and/or wherein the control electronics can deactivate or deactivates a DC/DC converter supplying electrical power to the electric motor, and to an electromechanical actuator and to a method for damping the movement of an electromechanical actuator.
H02P 23/04 - Arrangements or methods for the control of AC motors characterised by a control method other than vector control specially adapted for damping motor oscillations, e.g. for reducing hunting
B64C 13/50 - Transmitting means with power amplification using electrical energy
H02P 3/22 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter for stopping or slowing an AC motor by short-circuit or resistive braking
H02P 29/04 - Arrangements for regulating or controlling electric motors, appropriate for both AC and DC motors by means of a separate brake
31.
DEVICE FOR SUPPLYING PRESSURISED AIR TO A FUEL CELL CATHODE, WITH OPTIMISED COOLING
Disclosed is a device for supplying pressurised air to a cathode (110) of a fuel cell (100), comprising a compressor (12) connected to an air inlet pipe (14) and to an inlet (112) of the cathode, configured to receive air originating from the air inlet pipe (14), compress it and supply it to the cathode (110), a motor (16) configured to drive the compressor (12) and surrounded by a casing (18), a recovery turbine (26) configured to expand the water-laden air (24) originating from the outlet (114) of the cathode in order to supply this expanded air (28) via an outlet of the turbine (26).
Disclosed is a device for supplying pressurised air to a cathode (110) of a fuel cell (100), comprising a compressor (12) connected to an air inlet pipe (14) and to an inlet (112) of the cathode, configured to receive air originating from the air inlet pipe (14), compress it and supply it to the cathode (110), a motor (16) configured to drive the compressor (12) and surrounded by a casing (18), a recovery turbine (26) configured to expand the water-laden air (24) originating from the outlet (114) of the cathode in order to supply this expanded air (28) via an outlet of the turbine (26).
The device is characterised in that it comprises a cooling channel (32) configured to receive at least some of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
H02K 5/18 - Casings or enclosures characterised by the shape, form or construction thereof with ribs or fins for improving heat transfer
32.
Driven turbocompressor of an air conditioning system having optimized cooling
The invention relates to a driven turbocompressor of an air conditioning system, comprising a compressor (12) which is connected to an air intake duct (14) and to an inlet (112) of a cabin of a vehicle, and is configured to receive air from the air intake duct (14), to compress it and to provide it to the cabin, a motor (16) that is configured to drive the compressor (12) and is surrounded by a casing (18), a recovery turbine (26) that is configured to expand the cabin air (24) coming from an outlet (114) of the cabin. The device is characterized in that it comprises a cooling duct (32) configured to receive at least part of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).
The invention relates to a plate heat exchanger (1), configured for exchanging heat between a first fluid flowing through a first duct and a second fluid flowing through a second duct, wherein the fluids flow between two external plates (2), which plate heat exchanger comprises a plate exchanger unit comprising a plurality of internal plates (12, 14) that are arranged substantially parallel to one another, the internal plates being arranged substantially parallel to the external plates (2) and characterised in that it comprises at least one lateral encapsulation plate (20) extending substantially orthogonally to the internal plates, each lateral encapsulation plate being contactedly attached to the external plates (2) so as to laterally close the second duct.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
F28F 9/00 - CasingsHeader boxesAuxiliary supports for elementsAuxiliary members within casings
34.
HEAT EXCHANGER COMPRISING AT LEAST ONE LATERAL ENCASULATION PLATE, AIR CONDITIONING SYSTEM AND VEHICLE
The invention relates to a plate heat exchanger (1), configured for exchanging heat between a first fluid flowing through a first duct and a second fluid flowing through a second duct, wherein the fluids flow between two external plates (2), which plate heat exchanger comprises a plate exchanger unit comprising a plurality of internal plates (12, 14) that are arranged substantially parallel to one another, the internal plates being arranged substantially parallel to the external plates (2) and characterised in that it comprises at least one lateral encapsulation plate (20) extending substantially orthogonally to the internal plates, each lateral encapsulation plate being contactedly attached to the external plates (2) so as to laterally close the second duct.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
F28F 9/00 - CasingsHeader boxesAuxiliary supports for elementsAuxiliary members within casings
35.
HEAT-EXCHANGE DEVICE COMPRISING FLOW-LIMITING DEVICES, AIR-CONDITIONING SYSTEM AND VEHICLE
The invention relates to a heat-exchange device comprising: an exchanger block (12) arranged in a circulation chamber bounded by two external plates, said exchanger block comprising a first internal layer and a last internal layer allowing the circulation of the first heat-transfer fluid, said exchanger block comprising a plurality of internal plates (13, 14, 15, 16) arranged substantially in parallel with one another between two ends of said exchanger block, characterised in that each first internal layer and each last internal layer comprises at least one flow-limiting device (20) that is configured to be able to impede at least in part the circulation of said first fluid flow in said internal layer.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
The invention relates to a method for the treatment, in particular the surface finishing, of an inner surface of a component by means of a medium, in which method the component to be treated is placed at least partly within the medium and a relative movement is generated between the component and the medium surrounding the component. According to the invention, a flow guide is mounted in the region of an inlet opening of the component that is fluidically connected to the inner surface to be treated, said flow guide systematically directing part of the medium, moving relative to the component, into the inlet opening and hence to the inner surface to be treated. The present invention further relates to a device for performing the method according to the invention and to a method for producing a flow guide of a device according to the invention.
B05C 3/04 - Apparatus in which the work is brought into contact with a bulk quantity of liquid or other fluent material the work being immersed in the liquid or other fluent material with special provision for agitating the work or the liquid or other fluent material
B05C 3/09 - Apparatus in which the work is brought into contact with a bulk quantity of liquid or other fluent material the work being immersed in the liquid or other fluent material for treating separate articles
B05C 7/04 - Apparatus specially designed for applying liquid or other fluent material to the inside of hollow work the liquid or other fluent material flowing or being moved through the workApparatus specially designed for applying liquid or other fluent material to the inside of hollow work the work being filled with liquid or other fluent material and emptied
B05C 13/02 - Means for manipulating or holding work, e.g. for separate articles for particular articles
B65G 49/04 - Conveying systems characterised by their application for specified purposes not otherwise provided for for conveying workpieces through baths of liquid the workpieces being immersed and withdrawn by movement in a vertical direction
37.
SYSTEM FOR COOLING A FUEL CELL AND FUEL CELL EQUIPPED WITH SUCH A SYSTEM
The invention relates to a system for cooling a fuel cell (10) of a transport vehicle such as an aircraft, comprising: a cooling heat exchanger (30) configured to be able to exchange heat between a loop (20) for cooling the cell and a channel for circulating dynamic air; a device (22, 23) for recovering water produced by said fuel cell; a tank (25) for storing recovered water; a device (50) for spraying water into said dynamic air channel (40) upstream of said heat exchanger (30); and a computer (28) for controlling the amount of sprayed water on the basis of a measurement representing the temperature of said fuel cell (10).
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04992 - Processes for controlling fuel cells or fuel cell systems characterised by the implementation of mathematical or computational algorithms, e.g. feedback control loops, fuzzy logic, neural networks or artificial intelligence
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
characterized in that each plate extends along a non-planar surface following at least a first oscillating curve, and each fin further following at least one second oscillating curve along at least one second main direction, in such a way that each passage path allows the fluid to flow in the closed space along a fluid direction defined by a generatrix that is a combination at least of the first oscillating curve and the second oscillating curve.
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/06 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being attachable to the element
39.
AIRCRAFT ENGINE SUSPENSION PYLON PROVIDED WITH A COUNTERFLOW COOLING EXCHANGER
The invention relates to an aircraft pylon comprising a counterflow cooling exchanger (10) for cooling a stream of hot primary air (22) by a stream of cold secondary air (24) flowing in opposite directions to one another in a longitudinal direction (L), characterised in that it comprises two bundles (10a, 10b) juxtaposed on either side of a central axis (12) and each comprising a plurality of longitudinal parallel plates (15) which form a hot pass and a cold pass of the bundle, and in that one of the hot or cold passes of each bundle is fed by a central inlet (14a) common to the two bundles (10a, 10b) and one of the hot or cold passes of each bundle opens into a central outlet (16) common to the two bundles, said inlets (14b, 14c) and outlets (16b, 16c) of the combined passes, referred to as lateral inlets and outlets, being separated and diverging laterally from said central axis (12).
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
40.
AIRCRAFT ENGINE SUSPENSION PYLON PROVIDED WITH A COUNTERFLOW COOLING EXCHANGER
The invention relates to an aircraft pylon comprising a counterflow cooling exchanger (10) for cooling a stream of hot primary air (22) by a stream of cold secondary air (24) flowing in opposite directions to one another in a longitudinal direction (L), characterised in that it comprises two bundles (10a, 10b) juxtaposed on either side of a central axis (12) and each comprising a plurality of longitudinal parallel plates (15) which form a hot pass and a cold pass of the bundle, and in that one of the hot or cold passes of each bundle is fed by a central inlet (14a) common to the two bundles (10a, 10b) and one of the hot or cold passes of each bundle opens into a central outlet (16) common to the two bundles, said inlets (14b, 14c) and outlets (16b, 16c) of the combined passes, referred to as lateral inlets and outlets, being separated and diverging laterally from said central axis (12).
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
41.
Air conditioning system for a cabin of an air or rail transport vehicle using a pneumatic and thermal air source which is separate from the air conditioning source
b) of said power turbine (4) and said ram-air circulation channel (13) upstream of said primary exchanger (PHX) so that said bleed air expanded by said power turbine (4) can form a thermal energy source for said ram air being supplied to said primary circuit of said primary exchanger (PHX).
In order to reduce maintenance work and to improve long-time reliability, the invention provides a health monitoring method for checking a functionality of a flight control surface driving apparatus (104) using at least one load sensor (110) for sensing a load imposed on a control surface drive device (106), the method comprising at least one of the steps: a) comparing at least one load sensor output signal (62-1) of the at least one load sensor (110) with at least one first threshold (T1-L, T1-U) while operating the control surface drive device (106) to move the at least one control surface (102) to a predetermined extended position, b) comparing at least one load sensor output signal (62-1, 62-2) of the at least one load sensor (110) with at least one second threshold (T2-L, T2-U) while operating the control surface drive device (106) to move the at least one control surface (102) from an extended position to a retracted position. Further, a flight control surface drive apparatus (104), a flight control system (100) and an aircraft (10) comprising a control device (112) configured to automatically conduct such health monitoring method are described.
In order to reduce maintenance work and to improve long-time reliability, the invention provides a health monitoring method for checking a functionality of a flight control surface driving apparatus (104) using at least one load sensor (110) for sensing a load imposed on a control surface drive device (106), the method comprising at least one of the steps: a) blocking movement of the transmission device (108) by means of a brake device (118), b) commanding the control surface drive device (106) to apply a load on the blocked transmission device (108), and c) determining whether at least one load sensor output signal (62) of the at least one load sensor (110) is within a predetermined range. Further, a flight control surface drive apparatus (104), a flight control system (100) and an aircraft (10) comprising a control device (112) configured to automatic command conduct of such health monitoring method are described.
Method for manufacturing a fire-resistant part of an air conditioning system for an air or rail transport vehicle, characterized in that it includes at least the following steps: a step of obtaining a part including at least one aluminum alloy surface portion, and a step of treating the aluminum alloy surface portion by use of micro-arc oxidation in order to produce a ceramic coating on the surface portion.
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F16K 25/00 - Details relating to contact between valve members and seats
The invention relates to an electrical air conditioning system for air conditioning a cabin (10) of an aircraft comprising a source (11) of fresh air, a dynamic air circulation duct (12), a motorized compressor (13) comprising an air inlet connected to said source of fresh air, and an air outlet connected to a primary cooling exchanger (PHx) housed in said dynamic air duct; an air cycle turbomachine (14) comprising at least a first compressor (15) and a first turbine (17) that are mechanically coupled to one another, said first compressor comprising an air inlet that can be connected either to said primary cooling exchanger (PHx) or to said source (11) of fresh air, and an air outlet connected to a main cooling exchanger (MHx) housed in said dynamic air duct, said first turbine (17) comprising an air inlet that can be connected either to a discharge port (54) for discharging stale air from said cabin or to said main cooling exchanger (MHx), and an air outlet that can be connected either to said cabin (10) or to an air injector (52) opening into said dynamic air duct.
Heat exchanger assembly comprising a ram air flow channel (14) extending in a longitudinal direction, and characterized in that said assembly comprises: at least two separate heat exchangers (12a, 12b) that are adjacent in a transverse direction perpendicular to the longitudinal direction, are arranged in the ram air flow channel (14), and are configured such that the ram air passing through said channel (14) forms a cold pass of each heat exchanger (12a, 12b) by passing through said heat exchanger (12a, 12b) in said longitudinal direction, each heat exchanger (12a, 12b) also being configured for the passage therethrough of a fluid that is intended to be cooled and that forms a hot pass (20a, 20b); and an air passage which is provided between the heat exchangers and forms a thermally insulating air gap (18) between said exchangers (12a, 12b), and through which the ram air flows, said air passage extending in said longitudinal direction of said ram air flow channel (14).
The invention relates to a method for installing coil groups in an electric machine (100), each coil group (104, 204) comprising at least one coil, each coil being composed of a plurality of turns of conductors, characterised in that it comprises, for each coil group (104, 204), the following installation steps applied to each coil group before being applied to the following coil group: a step of inserting a first coil group into at least two free or partially occupied slots (106) of the electric machine (100), the coil portions arranged outside the slots forming the coil heads, and a final shaping step in which the heads of the coils of said coil group are compacted into a predetermined shape, by a preconfigured tool.
H02K 3/38 - Windings characterised by the shape, form or construction of the insulation around winding heads, equalising connectors, or connections thereto
H02K 15/00 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
H02K 15/10 - Applying solid insulation to windings, stators or rotors, e.g. applying insulating tapes
48.
DEVICE FOR SUPPLYING A PLURALITY OF CATHODES OF A FUEL CELL SYSTEM
The invention relates to a device for supplying pressurized air to a plurality of cathodes (100a-100d) of a fuel cell system, characterized in that it comprises a motorized compressor (12) configured to provide a source of pressurized air to all the cathodes (100a-100d), a set of ducts configured to duct the pressurized air towards each cathode (100a-100d), for each cathode (100a-100d), a proportional valve (20a-20d) upstream or downstream of said cathode (100a-100d) and configured to regulate the flow rate of pressurized air passing through said cathode (100a-100d), anti-surge protection means (30, 32) configured to allow the circulation of a minimal flow rate of pressurized air leaving the compressor (12), and a control device (24) configured to control the speed of the compressor (12) and the opening or closing of each proportional valve (20a-20d) and/or the operation of the anti-surge protection means (30, 32).
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
The invention relates to a device for supplying pressurized air to a plurality of cathodes (100a-100d) of a fuel cell system, characterized in that it comprises a motorized compressor (12) configured to provide a source of pressurized air to all the cathodes (100a-100d), a set of ducts configured to duct the pressurized air towards each cathode (100a-100d), for each cathode (100a-100d), a proportional valve (20a-20d) upstream or downstream of said cathode (100a-100d) and configured to regulate the flow rate of pressurized air passing through said cathode (100a-100d), anti-surge protection means (30, 32) configured to allow the circulation of a minimal flow rate of pressurized air leaving the compressor (12), and a control device (24) configured to control the speed of the compressor (12) and the opening or closing of each proportional valve (20a-20d) and/or the operation of the anti-surge protection means (30, 32).
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
A method and a system are provided for monitoring the state of a heat exchanger (17) in an air circuit (5) of an aircraft (7), the heat exchanger being intended to cool the air extracted from a source of a main hot air source of the aircraft. An acquisition module (11) is configured to acquire temperature measurements taken by a probe disposed at an outlet of said heat exchanger, the acquisition being carried out when the air circuit is supplied by a secondary hot air source downstream of the heat exchanger and the main hot air source being turned off. A processor (9) is configured to select a relevant temperature measurement from the temperature measurements and to detect a possible leak in the heat exchanger (17) by comparing the relevant temperature measurement to a predetermined alert threshold.
G01M 3/00 - Investigating fluid tightness of structures
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64F 5/60 - Testing or inspecting aircraft components or systems
The invention relates to a regulator, configured to receive a stream of hot air carrying pneumatic power via an air inlet (12), to treat this hot air and to send the treated hot air to an air outlet (14) configured 5 to supply a pneumatic actuator (16), comprising a reference pressure source and an air expansion device comprising a diaphragm (22), the diaphragm (22) being configured to control the flow rate of the hot air stream by comparing the pressure of said hot air stream with the reference pressure of the reference pressure source. The regulator is characterized in that it 10 comprises an air intake (24) configured to receive a cold source, and a pipe (25) for guiding the cold source to the diaphragm (22), so that the cold source forms the reference pressure source and a source for cooling the diaphragm (22).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F25B 9/00 - Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
53.
Heat exchanger of an air-conditioning system of a cabin of an aircraft, and system comprising such a heat exchanger
Heat exchanger of an air-conditioning system of a cabin of a transport vehicle, comprising: a primary circuit supplied by a first air flow, a secondary circuit supplied by a second air flow, a casing defining an air-circulation enclosure, a primary circuit inlet box allowing entry into said air-circulation enclosure, and a primary circuit outlet box allowing exit from the air-circulation enclosure, characterized in that said inlet box is mounted removably on said casing, and in that it houses a three-dimensional structure forming a catalytic and/or adsorbent support for treating the air of said primary circuit, and a means for distributing said first air flow into said heat-exchange matrix.
Air conditioning system for a cabin of an air or rail transport vehicle, comprising: a pneumatic turbine engine that comprises at least one compressor and at least one turbine (126) and is connected by a mechanical shaft extending along an axis, referred to as the turbine engine axis (132), said turbine comprising an air inlet and an air outlet; and a water extraction loop that comprises a heater (110), a condenser (112) and a water separator (114), is fluidically arranged between an air outlet of the compressor and the air inlet of said turbine (126), and is configured to dry the air supplied to said turbine (126), characterized in that said heater (110), said condenser (112), and said water separator (114) are arranged in series on the turbine engine axis (132) or around said axis, forming the air inlet of said turbine (126).
The invention relates to a regulator, configured to receive a hot air flow via an air inlet (12), to treat this hot air and to transmit the treated hot air to an air outlet (14) configured to supply a pneumatic actuator (16), comprising at least one temperature-sensitive electrical and/or mechanical element (36, 37), and a regulator body (100). The regulator is characterized in that the regulator body is composed of a heat-conducting hollow enclosure (28) at least partially surrounding a duct (22) for transporting the hot air flow, said cavity being at least partially filled with a metal mesh produced by additive manufacturing that allows the cooling air to circulate, and in that the temperature-sensitive electrical and/or mechanical element (36, 37) is arranged in, or in contact with, the regulator so as to be cooled by the cooling air by thermal conduction.
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
F16K 49/00 - Means in or on valves for heating or cooling
B33Y 80/00 - Products made by additive manufacturing
56.
DISTRIBUTED PNEUMATIC SUPPLY SYSTEM OF AN AIRCRAFT
The invention relates to an air system for an aircraft, that includes air consumers; air sources and a network of ducts and associated control valves controlled by a control unit. The air system is characterized in that: the network of ducts and associated valves includes at least one isolation valve, arranged between an air bleed device and an air duct connecting an air conditioning pack and an auxiliary power unit; the control unit is configured to be able to determine an ideal configuration of the control valves according to the identified requirements of each consumer and a degraded configuration that makes it possible to supply air to predetermined air consumers from the available air sources when the ideal configuration is not attainable.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
The invention relates to an air conditioning system for an aircraft cabin, comprising two motorized turbomachines (16a, 16b) each comprising a compressor (14a, 14b) supplying an outlet (24) common to the compressors and a turbine, one of the turbines, referred to as water extraction turbine (16a), being dedicated to a water extraction loop (28) and the other turbine, called cooling turbine (16b), helping cool the air.
The invention relates to an air conditioning system for an aircraft cabin, comprising two motorized turbomachines (16a, 16b) each comprising a compressor (14a, 14b) supplying an outlet (24) common to the compressors and a turbine, one of the turbines, referred to as water extraction turbine (16a), being dedicated to a water extraction loop (28) and the other turbine, called cooling turbine (16b), helping cool the air.
The air conditioning system comprises a network of pipes and associated valves, connected to the common outlet (24) of the compressors and making it possible to supply, from the common outlet of the compressors:
either the inlet (160) of the water extraction turbine (16a), or the inlet (164) of the cooling turbine (16b), bypassing the turbine (16a) and the water extraction loop,
or an outlet (60) of the air conditioning system directly, bypassing the cooling turbine (16b) and the water extraction turbine (16a).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
58.
METALLIC COMPONENT AND METHOD OF COATING SAID METALLIC COMPONENT
The invention relates to a metallic component having a corrosion protection film and a wear protection film, wherein the corrosion protection film covers a first zone and the wear protection film covers a second zone of the surface of the component adjacent to the first zone, with a film run-out of the wear protection film covering a marginal region of the corrosion protection film at the boundary between the first and second zones.
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C25D 5/36 - Pretreatment of metallic surfaces to be electroplated of iron or steel
59.
HEAT EXCHANGER WITH CLOSING BAR OPTIMISED FOR ICE PROTECTION
Disclosed is a plate heat exchanger, for heat exchange between a hot fluid and a cold fluid, comprising at least one bundle edge (130a, 130b) for maintaining the sealing, a plurality of closure bars (138) defining, with the closure plates, flow channels, characterised in that the bundle edge (130a) arranged at a cold pass inlet and a hot pass inlet comprises a hot air supply inlet (132), and in that at least one closure bar (138) arranged in the length of the cold pass inlet comprises an inlet for the hot air and a flow circuit for the hot air that is a U-shaped and comprises two sections each extending over the entire length of the closure bar, a hot air outlet for rejecting the hot air in the hot pass, and an intermediate section forming the base of the U.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
60.
Method of monitoring an electrohydrostatic actuator
The disclosure relates to a method of monitoring an electrohydrostatic actuator, wherein the electrohydrostatic actuator comprises a hydraulic pump drivable by an electric motor and a hydraulic activator drivable by means of the hydraulic pump to move a component, in particular an aircraft part. The method include detecting the instantaneous speed of the electric motor; detecting an instantaneous position of the activator; detecting a parameter that relates to an instantaneous operating point of the electrohydrostatic actuator; determining a state variable relating to an efficiency of the electrohydrostatic actuator on the basis of at least the detected speed and the detected position in dependence on the detected parameter; and determining a state of the electrohydrostatic actuator on the basis of the currently determined value.
d) designed to provide heat exchanges between a second oil circuit (28) and the flow air (206; 208), allowing the heat from said second oil circuit (26) to be transferred to the flow air (206; 208); and at least one circuit (30) connecting the first oil circuit (26) and said second oil circuit (28).
The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.
B64C 13/50 - Transmitting means with power amplification using electrical energy
B64C 13/28 - Transmitting means without power amplification or where power amplification is irrelevant mechanical
F15B 13/04 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
F15B 13/043 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor operated by fluid pressure with electrically-controlled pilot valves
B64C 13/40 - Transmitting means with power amplification using fluid pressure
F15B 21/08 - Servomotor systems incorporating electrically- operated control means
63.
SYSTEM AND METHOD FOR COOLING A FUEL CELL ASSEMBLY
The invention relates to a system for cooling a fuel cell assembly (10) of a transport vehicle, such as an aircraft, comprising: a coolant circulation loop (20); a cooling heat exchanger (24) configured to be able to provide heat exchanges between said loop (20) and a channel (25) for circulating a cooling air (26); a variable-speed pump (21) for supplying said cooling loop with coolant as a function of a measurement representative of the cooling need of said fuel cell assembly; for each fuel cell (10a, 10b, 10c) of said cell assembly, a 3-way valve (12a, 12b, 12c) for regulating the flow rate of coolant supplying this cell as a function of a measurement representative of the cooling need of this cell.
H01M 8/249 - Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
64.
DEVICE FOR FILTERING AIR INTENDED TO SUPPLY AN AIR SYSTEM OF A TRANSPORT VEHICLE, SYSTEM COMPRISING SUCH A DEVICE, AND METHOD FOR MANUFACTURING SUCH A FILTERING DEVICE
SAINT-GOBAIN CENTRE DE RECHERCHES ET D'ETUDES EUROPEEN (France)
Inventor
Héraud, Philippe
Dreibine, Lamia
Jacquart, Jérôme
Nguyen Van Nuoi, Patrick
Giardella, Lucas
Abstract
Device (50) for filtering air intended to supply an air system of an air-transport vehicle, rail vehicle or motor vehicle, characterized in that it comprises a porous three-dimensional structure (52) comprising at least one portion intended to be in contact with said air to be filtered, termed exchange portion (53), said exchange portion (53) comprising at least one adsorbent material in the form of particles chosen from carbon, a zeolite, a metal organic framework and mixtures thereof, said adsorbent particles being connected by a binder, said binder comprising at least one material chosen from the group consisting of boehmite, hydrated aluminas, transition aluminas and mixtures thereof.
B01D 53/04 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by adsorption, e.g. preparative gas chromatography with stationary adsorbents
B01J 20/20 - Solid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof comprising inorganic material comprising free carbonSolid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof comprising inorganic material comprising carbon obtained by carbonising processes
B01J 20/22 - Solid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof comprising organic material
B01J 20/28 - Solid sorbent compositions or filter aid compositionsSorbents for chromatographyProcesses for preparing, regenerating or reactivating thereof characterised by their form or physical properties
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B01J 20/30 - Processes for preparing, regenerating or reactivating
MODULE FOR SUPPLYING PRESSURISED FRESH AIR TO AN AIR-CONDITIONING PACK OF AN AIRCRAFT CABIN, AIR-CONDITIONING SYSTEM EQUIPPED WITH SUCH A MODULE AND CORRESPONDING METHOD
The invention relates to an air conditioning system for an aircraft cabin (5), comprising: an engine air bleed device (10); an air conditioning pack (20) comprising a pack air inlet (21) connected to the engine bleed device (10), and a pack air outlet (22) connected to the cabin (5); an auxiliary module (50) for supplying pressurised air comprising an auxiliary turbomachine (51) comprising a compressor (52) supplied with outside fresh air and a turbine capable of being supplied with air originating from the engine bleed device; and a control unit configured to activate either a standard mode in which the pack air inlet is supplied with pressurised air originating from the engine bleed device (10), or a fresh air mode in which the pack air inlet (21) is supplied with pressurised air originating from the auxiliary module (50).
Disclosed is a system for protecting an outer surface of an aircraft from icing, comprising at least two fuel cells (112, 212), characterised in that it comprises a first and a third liquid circuit (114, 214) each circulating a coolant for cooling the fuel cells (112, 212), a second and a fourth liquid circuit (118a, 118b) each circulating an anti-icing liquid, at least two anti-icing heat exchangers (120a-d, 220a-d) arranged on the outer surface of the aircraft and passed through by each anti-icing liquid when it circulates in the second or the fourth liquid circuit (118a, 118b), and two liquid-liquid heat exchangers (116, 216) in which the coolants form a hot pass and the icing-protection liquids form a cold pass in order to warm the icing-protection liquid by the heat of the coolant.
INSTITUT SUPERIEUR DE L'AERONAUTIQUE ET DE L'ESPACE (France)
Inventor
Roncen, Thomas
Manet, Vincent
Michon, Guilhem
Abstract
Vibration absorbing device comprising a housing (12), a membrane (14) embedded in the housing (12) and thus forming two chambers (18a, 18b) in the housing (12), the chambers (18a, 18b) being filled with a fluid, at least one weight (16) arranged on the membrane (14) such that a movement of the weight (16) causes a movement of the membrane (14), and at least one duct (24) arranged to allow the fluid to flow between the two chambers (18a, 18b) in the event of movement of the membrane (14) and the weight (16).
Exchanger (16) for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels (80) for the circulation of the secondary air; and a plurality of channels for the circulation of the primary air, characterized in that said exchanger further comprises: water circulation channels (83) each extending adjacently to a secondary channel (80); water-spray micro-perforated hollow bars (63) each extending adjacently to a primary channel (60) and fluidically connected to the micro-perforated hollow bars in order to be able to heat the water by interaction with the primary air before said water is sprayed into the flow of primary air at the inlet of the exchanger.
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
69.
Device for cooling heat-sensitive control members of a pneumatic or electropneumatic valve, and valve equipped with such a cooling device
The invention relates to a device (30) for cooling heat-sensitive control members (29) of a pneumatic or electropneumatic valve (20), comprising a containment casing (31) designed to contain said control members (29): a fresh air inlet (32) in said containment casing (31); an air outlet (33) of said containment casing, provided with a ventilation air tube (34) that comprises: an air acceleration column (35) which puts into fluidic communication said containment casing (31) and the air outlet (33); a primary supply (37) for supplying the acceleration column (35) with primary air; a secondary supply (38) for supplying the acceleration column (35) with secondary air, provided in said containment casing (31) such that the primary air can drive and accelerate the secondary air in the direction of the air outlet so as to produce forced air ventilation in said containment casing (31) between the air inlet (32) and the air outlet (33).
F16K 49/00 - Means in or on valves for heating or cooling
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F28F 13/06 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
70.
Distributor for a turbomachine radial turbine, turbomachine comprising such a distributor and air conditioning system comprising such a turbomachine
The invention relates to a distributor for a turbomachine radial turbine, comprising an annular grill (26) extending about a central axis (10) and comprising a plurality of variable-pitch blades (31), defining between them an air passage cross section, characterized in that each blade is rotatably mounted about a pivot shaft (32), itself moveable in a translation direction, comprising at least one radial component, such that said blade may, upon actuation of control means (40), be pivoted about the pivot shaft and/or moved in relation to the central axis in said translation direction so as to be able to modify the air passage cross section by respectively controlling the metal angle (α3) and the radial spacing (ΔR).
F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
F04D 29/46 - Fluid-guiding means, e.g. diffusers adjustable
71.
Air conditioning system for an aircraft cabin, comprising means for reheating the water collected by the water extraction loop
Air conditioning system for a cabin (10) of an aircraft, comprising: an air bleed device; an air cycle turbine engine (12); at least one main cooling exchanger (16); a water extraction loop (30); and a pipe (26) for distributing water extracted by said extraction loop (30), characterized in that said system further comprises means (40) for heating the water extracted by the water extraction loop so as to be able to spray the water into a ram-air channel (22) which supplies said main exchanger (16).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
Disclosed is a device for supplying pressurised air to a cathode (110) of a fuel cell (100), comprising a compressor (12) connected to an air inlet pipe (14) and to an inlet (112) of the cathode, configured to receive air originating from the air inlet pipe (14), compress it and supply it to the cathode (110), a motor (16) configured to drive the compressor (12) and surrounded by a casing (18), a recovery turbine (26) configured to expand the water-laden air (24) originating from the outlet (114) of the cathode in order to supply this expanded air (28) via an outlet of the turbine (26). The device is characterised in that it comprises a cooling channel (32) configured to receive at least some of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
73.
DRIVEN TURBOCOMPRESSOR OF AN AIR CONDITIONING SYSTEM, HAVING OPTIMIZED COOLING
The invention relates to a driven turbocompressor of an air conditioning system, comprising a compressor (12) which is connected to an air intake duct (14) and to an inlet (112) of a cabin of a vehicle, and is configured to receive air from the air intake duct (14), to compress it and to provide it to the cabin, a motor (16) that is configured to drive the compressor (12) and is surrounded by a casing (18), a recovery turbine (26) that is configured to expand the cabin air (24) coming from an outlet (114) of the cabin. The device is characterized in that it comprises a cooling duct (32) configured to receive at least part of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).
d), and suitable for being able to be supplied with a third fluid, referred to as intermediate fluid, brought to a third temperature, different from said first temperature.
F28D 7/10 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged one within the other, e.g. concentrically
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
75.
Loop for extracting water from an air conditioning system of a cabin of an air or rail transport vehicle
The invention relates to a loop (40) for extracting water from an air conditioning system of a cabin (5) of an air or rail transport vehicle comprising an air cycle turbine engine (20), the loop comprising: a condenser (41); a three-dimensional mesh grid (45) housed in an outlet box (42) of the condenser and configured to be able to capture water droplets in a stream of moist air condensed by the condenser; a water recovery unit (46) opening on the condenser outlet box (42) and arranged under the three-dimensional mesh grid (45) so as to be able to recover, by force of gravity, the water collected by the three-dimensional mesh grid (45); an air return pipe (44) linking the outlet box (42) to a supply interface for directly or indirectly supplying the turbine of the air conditioning system.
The invention relates to a system for cooling a fuel cell (10) of a transport vehicle, such as an aircraft, comprising a cooling heat exchanger (30) configured to be able to exchange heat between a loop (20) for cooling the cell and a channel for circulating dynamic air; a device (22, 23) for recovering water produced by the fuel cell; a tank (25) for storing recovered water; a device (50) for spraying water into the dynamic air channel (40) upstream of the heat exchanger (30); a computer (28) for controlling the amount of sprayed water as a function of a measurement representing the temperature of the fuel cell (10).
H01M 8/04014 - Heat exchange using gaseous fluidsHeat exchange by combustion of reactants
B64D 37/00 - Arrangements in connection with fuel supply for power plant
H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
H01M 8/04992 - Processes for controlling fuel cells or fuel cell systems characterised by the implementation of mathematical or computational algorithms, e.g. feedback control loops, fuzzy logic, neural networks or artificial intelligence
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
77.
PROCESS FOR TREATING THE SURFACE OF A PART MADE OF ALUMINIUM OR ALUMINIUM ALLOY OR OF MAGNESIUM OR MAGNESIUM ALLOY
The invention relates to a method for the surface treatment of a part made from aluminum or aluminum alloy or from magnesium or magnesium alloy, comprising a step of treatment by oxidation of said part and a step of applying an aqueous composition to the surface of said part.
The invention relates to a heat exchanger that is configured to permit an exchange of heat between a first fluid and a second fluid that circulate in passage paths formed by plates (14a, 14b) and fins (16a, 16b) of the heat exchanger, the fluids flowing in a multitude of passage channels (10) each consisting of a closed space (12) delimited by two adjacent plates and two adjacent fins, characterized in that each plate extends along a non-planar surface following at least one oscillating curve, and each fin further following at least one second oscillating curve along at least one second main direction, in such a way that each passage path allows the fluid to flow in the closed space along a fluid direction defined by a generatrix that is a combination at least of the first oscillating curve and the second oscillating curve.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
F28F 3/06 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being attachable to the element
81.
System and method for cooling a fluid of a lubrication or cooling circuit of a drive unit of an aircraft, and aircraft propulsion engine provided with such a cooling system
The invention relates to a system for cooling a fluid of a circuit (20) for lubricating a propulsion engine (10) of an aircraft, the engine comprising a nacelle (11) which extends in a longitudinal direction (X) between an air inlet opening (12) and an ejection nozzle (13), a turbomachine (14) having a casing (15) secured inside said nacelle by rectifier arms (16), and a fan (17) arranged at said air inlet opening (12) of said nacelle, upstream of said turbomachine (14), and designed to be able to generate a primary air flow feeding said turbomachine and a secondary air flow feeding a channel, referred to as a secondary channel (18), formed between said nacelle (11) and said casing (15) of said turbomachine, characterized in that said cooling system comprises a skin exchanger (30) which is arranged on an inner wall of said nacelle (11), longitudinally between said air inlet opening (12) of said nacelle and said rectifier arms (16), said skin exchanger being in fluid communication with said fluid circuit and designed to be able to provide heat exchanges between said lubricating fluid and the air flowing through said secondary channel.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
82.
AIR-CONDITIONING SYSTEM FOR A CABIN OF AN AIR OR RAIL TRANSPORT VEHICLE USING A PNEUMATIC AND THERMAL AIR SOURCE SEPARATE FROM THE AIR-CONDITIONING SOURCE
The invention relates to an air-conditioning system for a cabin (10) of an aircraft (80) comprising a bleed air source (12); a dynamic air circulation channel (13); a network of ducts and control valves; an air-cycle turbomachine comprising at least one compressor (3) and a power turbine (4) mechanically connected to one another; at least one primary heat exchanger (PHX) housed in said channel (13), characterised in that said network of ducts comprises a thermal power duct (53) suitable for being able to fluidly connect, upon operating at least one control valve (25, 21), said air outlet (4b) of said power turbine (4) and said dynamic air circulation channel (13) upstream of said primary exchanger (PHX) so that said bleed air expanded by said power turbine (4) can form a source of thermal energy for said dynamic air feeding said primary circuit of said primary exchanger (PHX).
The invention relates to a method for supplying air at a controlled temperature to a cabin of a surface vehicle in which at least one air cycle device is used, comprising at least one motorized turbocompressor. The air inlet of the turbine is arranged to receive a compressed airflow from the compressor. At least one exchanger is interposed between the air outlet of the compressor and the air inlet of the turbine. The air inlet of the compressor is arranged to receive air at a pressure greater than or equal to atmospheric pressure. The invention likewise relates to a surface vehicle comprising at least one such air cycle device.
A fluid flow control valve includes a valve body, a closing member arranged in the valve body and configured so that it can have at least one first position, called the open position, in which it allows the flow of fluid to flow freely in the valve body, and at least one second position, called the closed position, in which it prevents the fluid flow from flowing in the valve body between the fluid inlet and the fluid outlet, an electric actuator of the closing member that is suitable for being able to control the position of the closing member in the valve body, characterized in that the electric actuator is arranged in the valve body so that it can be cooled by the flow of fluid flowing in the valve body.
F16K 5/04 - Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having cylindrical surfacesPackings therefor
F16K 31/06 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a magnet
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B61D 27/00 - Heating, cooling, ventilating, or air-conditioning
F16K 31/04 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a motor
85.
Air sampling system equipped with an overpressure valve
The invention relates to an air bleed system comprising an air bleed port provided on an engine of an aircraft, an air supply pipe, a pressure sensor, a pressure relief valve mounted in said air supply pipe, characterized in that said pressure relief valve comprises: a valve body (11); a closure member (121) pivotally mounted in said air circulation duct; and an air discharge channel (13) passing through said valve body (11); at least one air discharge opening (15) formed on said upstream face of said closure member (121) and at least one air evacuation opening (19) which opens out to the outside of the air circulation duct.
F16K 5/04 - Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having cylindrical surfacesPackings therefor
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
F16K 11/085 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only taps or cocks with cylindrical plug
86.
METHOD FOR MANUFACTURING A FIRE-RESISTANT PART OF AN AIR CONDITIONING SYSTEM AND PART PRODUCED BY SUCH A METHOD
Method for manufacturing a fire-resistant part of an air conditioning system (9) for an air or rail transport vehicle (8), characterised in that it comprises at least the following steps: a step (10) of obtaining a part comprising at least one aluminium alloy surface portion, and a step (20) of treating the aluminium alloy surface portion by means of micro-arc oxidation in order to produce a ceramic coating on the surface portion.
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
C23C 4/02 - Pretreatment of the material to be coated, e.g. for coating on selected surface areas
C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
C23C 24/04 - Impact or kinetic deposition of particles
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
Air conditioning system for a cabin of an air or rail transportation vehicle comprising a pneumatic turbomachine comprising at least one compressor and at least one turbine (126) connected by a mechanical shaft extending along an axis, referred to as the turbomachine axis (132), the turbine comprising an air inlet and an air outlet, and a water extraction loop comprising a heater (110), a condenser (112), and a water separator (114), fluidly arranged between an air outlet of the compressor and the air inlet of the turbine (126), configured to dry the air supplied to the turbine (126), characterized in that the heater (110), the condenser (112) and the water separator (114) are arranged in a series on the axis or about the axis (132) of the turbomachine, forming the air inlet of the turbine (126).
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B61D 27/00 - Heating, cooling, ventilating, or air-conditioning
88.
HEAT EXCHANGER OF AN AIR-CONDITIONING SYSTEM OF A CABIN OF AN AIRCRAFT, AND SYSTEM COMPRISING SUCH A HEAT EXCHANGER
Heat exchanger of an air-conditioning system of a cabin of a transport vehicle, comprising: a primary circuit supplied by a first air flow (169), a secondary circuit supplied by a second air flow (168), a casing (161) defining an air-circulation enclosure (162), a primary circuit inlet box (164) allowing entry into said air-circulation enclosure, and a primary circuit outlet box (165) allowing exit from the air-circulation enclosure, characterized in that said inlet box (164) is mounted removably on said casing (161), and in that it houses a three-dimensional structure (163) forming a catalytic and/or adsorbent support for treating the air of said primary circuit, and a means for distributing said first air flow into said heat-exchange matrix.
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
Air conditioning system for an aircraft cabin, comprising a primary exchanger (14) configured to cool collected air (12) originating from at least one aircraft compressor, a pre-compressor (18), an intermediate exchanger (20), a main compressor (22) configured to compress the collected pre-compressed air, a main exchanger (28) configured to cool the collected compressed air, and a water extraction loop, characterised in that the system comprises a pipe (108) for recovering at least part of the air from the cabin after it has passed through the cabin, and pipes for circulating the recovered air which are configured such that the recovered air consecutively passes through a secondary exchanger (34), the recovered air forming a first cold source for cooling the collected air again, a heat exchanger (20), the recovered air forming a second cold source for cooling the collected air, a turbine (48) for recovering energy, the recovered air forming an energy source.
Air conditioning system for an aircraft cabin, comprising a primary exchanger (14) configured to cool collected air (12) originating from at least one aircraft compressor, a pre-compressor (18), an intermediate exchanger (20), a main compressor (22) configured to compress the collected pre-compressed air, a main exchanger (28) configured to cool the collected compressed air, and a water extraction loop, characterised in that the system comprises a pipe (108) for recovering at least part of the air from the cabin after it has passed through the cabin, and pipes for circulating the recovered air which are configured such that the recovered air consecutively passes through a secondary exchanger (34), the recovered air forming a first cold source for cooling the collected air again, a heat exchanger (20), the recovered air forming a second cold source for cooling the collected air, a turbine (48) for recovering energy, the recovered air forming an energy source.
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
91.
METHOD AND A SYSTEM FOR MONITORING THE STATE OF AN EXCHANGER IN AN AIR CIRCUIT OF AN AIRCRAFT
The invention relates to a method and a system for monitoring the state of a heat exchanger (17) in an air circuit (5) of an aircraft (7), the heat exchanger being intended to cool the air extracted from a main hot air source of the aircraft, the system comprising: - an acquisition module (11) configured to acquire temperature measurements taken by a probe arranged at an outlet of the heat exchanger, the acquisition being carried out when the air circuit is supplied by a secondary hot air source downstream of the heat exchanger and the main hot air source is disconnected, - a processor (9) configured to select a relevant temperature measurement from among the temperature measurements and to detect a possible leak in the heat exchanger (17) by comparing the relevant temperature measurement with a predetermined alert threshold.
The invention relates to an assembly of heat exchangers comprising a dynamic air flow channel (14) extending in a longitudinal direction and characterised in that it comprises at least two heat exchangers (12a, 12b) which are separated and adjacent in a transverse direction perpendicular to the longitudinal direction, arranged in the dynamic air flow channel (14), and configured so that the dynamic air passing through the channel (14) forms a cold pass of each heat exchanger (12a, 12b) by passing through the heat exchanger (12a, 12b) in said longitudinal direction, each heat exchanger (12a, 12b) also being configured to have a fluid to be cooled passing through it, forming a hot pass (20a, 20b), and an air passage formed between the heat exchangers forming a thermally insulating air gap (18) between the heat exchangers (12a, 12b), the air passage extending in the longitudinal direction of the dynamic air flow channel (14).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
93.
AIRCRAFT CABIN ELECTRICAL AIR CONDITIONING SYSTEM COMPRISING A MOTORIZED COMPRESSOR AND AN AIR CYCLE TURBOMACHINE
The invention relates to an electrical air conditioning system for air-conditioning a cabin (10) of an aircraft comprising a source (11) of fresh air, a dynamic air circulation duct (12), a motorized compressor (13) comprising an air inlet connected to said source of fresh air, and an air outlet connected to a primary cooling exchanger (PHx) housed in said dynamic air duct; an air cycle turbomachine (14) comprising at least a first compressor (15) and a first turbine (17) which are mechanically coupled to one another, said first compressor comprising an air inlet which can be connected either to said primary cooling exchanger (PHx) or to said source (11) of fresh air, and an air outlet connected to a main cooling exchanger (MHx) housed in said dynamic air duct, said first turbine (17) comprising an air inlet which can be connected either to a discharge port (54) for discharging stale air from said cabin or to said main cooling exchanger (MHx), and an air outlet which can be connected either to said cabin (10) or to an air injector (52) opening into said dynamic air duct.
A method for manufacturing an electrically conductive composite material includes obtaining a composite material which includes a thermoplastic matrix and short carbon fibers and is free of carbon nanotubes, preheating a furnace until a predetermined target temperature is reached, inserting the composite material into the preheated furnace once the target temperature has been reached, and heating the composite material in the furnace at the predetermined target temperature which is kept constant for a predetermined duration.
H01B 1/24 - Conductive material dispersed in non-conductive organic material the conductive material comprising carbon-silicon compounds, carbon, or silicon
B29B 9/14 - Making granules characterised by structure or composition fibre-reinforced
B29C 45/00 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mouldApparatus therefor
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
C08G 65/40 - Macromolecular compounds obtained by reactions forming an ether link in the main chain of the macromolecule from hydroxy compounds or their metallic derivatives derived from phenols from phenols and other compounds
B29K 71/00 - Use of polyethers as moulding material
B29K 105/12 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of short lengths, e.g. chopped filaments, staple fibres or bristles
The invention relates to a regulator, configured to receive a stream of hot air carrying pneumatic power via an air inlet (12), to treat this hot air and to send the treated hot air to an air outlet (14) configured to supply a pneumatic actuator (16), comprising a reference pressure source and an air expansion device comprising a diaphragm (22), the diaphragm (22) being configured to control the flow rate of the hot air stream by comparing the pressure of said hot air stream with the reference pressure of the reference pressure source. The regulator is characterised in that it comprises an air intake (24) configured to receive a cold source, and a pipe (25) for guiding the cold source to the diaphragm (22), so that the cold source forms the reference pressure source and a source for cooling the diaphragm (22).
The invention relates to a mechanical non-return mechanism for an aircraft application, wherein the aircraft application can be part of a flight control. The non-return mechanism comprises at least one drag brake, at least one main brake, and at least one ball ramp mechanism.
F16D 55/36 - Brakes with a plurality of rotating discs all lying side by side
B60T 7/12 - Brake-action initiating means for automatic initiationBrake-action initiating means for initiation not subject to will of driver or passenger
B60T 1/06 - Arrangements of braking elements, i.e. of those parts where braking effect occurs acting by retarding wheels acting otherwise than on tread, e.g. employing rim, drum, disc, or transmission
B64C 13/28 - Transmitting means without power amplification or where power amplification is irrelevant mechanical
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
A backstop of a torque transmission device of an aircraft steering system includes input and output sections of a drive shaft. Torque is transmitted from the input to the output, but is prevented from being transferred from the output back into the input. The input is limited from rotating coaxially relative to the output by more than a predetermined angle. The input stops at a first rotary position relative to the output upon rotating in a first rotary direction. The input stops at a second rotary position upon rotating in the opposite direction. The output is blocked from rotating in the second direction while the input is at the first rotary position and is blocked from rotating in the first direction while the input is at the second rotary position. The output is blocked from rotating by dissipating any torque acting upon the output into the housing of the backstop.
B64C 13/28 - Transmitting means without power amplification or where power amplification is irrelevant mechanical
F16C 19/04 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly
F16D 63/00 - Brakes not otherwise provided forBrakes combining more than one of the types of groups
The invention relates to a regulator, configured to receive a hot air flow via an air inlet (12), to treat this hot air and to transmit the treated hot air to an air outlet (14) configured to supply a pneumatic actuator (16), comprising at least one temperature-sensitive electrical and/or mechanical element (36, 37), and a regulator body (100). The regulator is characterized in that the regulator body is composed of a heat-conducting hollow enclosure (28) at least partially surrounding a duct (22) for transporting the hot air flow, said cavity being at least partially filled with a metal mesh produced by additive manufacturing that allows the cooling air to circulate, and in that the temperature-sensitive electrical and/or mechanical element (36, 37) is arranged in, or in contact with, the regulator so as to be cooled by the cooling air by thermal conduction.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
99.
Actuator system in an aircraft for monitoring a no-back brake
The present invention relates to an actuator system in an aircraft for monitoring a no-back brake, which system comprises an actuator for actuating a flap of a flight control system of the aircraft, a first torque sensor for detecting a torque on the drive side of the actuator, and a second torque sensor for detecting a torque on the output side of the actuator, wherein the actuator is provided with an auto-switching no-back brake to hold the flap actuated by the actuator in position. The actuator system further has a monitoring unit, which is connected to the first torque sensor and the second torque sensor and is designed to detect an acute or imminent fault condition of the no-back brake depending on an actuator state and the detected torque values of the first torque sensor and the second torque sensor.
The invention relates to a mechanical actuator for a high-lift system of an aircraft, wherein the actuator is provided with an internal gearing between an input and an output shaft and comprises an internal sensor for torque measurement, wherein the sensor comprises at least two sensing elements for detecting the input and output torque at separate measuring points, and a common evaluation unit for the at least two sensing elements.
B64C 13/34 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using toothed gearing
G01L 3/10 - Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft involving electric or magnetic means for indicating
