A heat exchanger of the air/oil type, for an annular air stream of a turbomachine, comprising a heat exchange zone with oil passages and heat exchange surfaces with the air, said heat exchange zone forming an axial air passage and having a profile facing the air flow and included in a plane perpendicular to said air flow, said profile of the exchange zone thermal being in an arc of a circle so as to be able to be arranged in the annular air stream, remarkable in that said heat exchanger comprises on a radially internal or external face of the exchange zone thermal, an oil inlet and an oil outlet, the oil passages comprising several paths between said oil inlet and said oil outlet, distributed along the profile in circular arc of the heat exchange zone.
An axial turbomachine, comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called a secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow, the tertiary flow being in a tertiary flow vein radially external to said primary flow, delimited by an internal wall and an external wall; and an air/oil type heat exchanger, disposed in the tertiary flow vein. The heat exchanger comprises several angular sectors, each angular sector comprising an oil inlet on the internal wall at an angular end of said sector, and an oil outlet on said internal wall at an opposite angular end of said sector.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F28D 7/08 - 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 otherwise bent, e.g. in a serpentine or zig-zag
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
3.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
An axial turbomachine comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a flow of radially external air, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow flow in a tertiary flow vein radially external to said primary flow; and a heat exchanger disposed in the tertiary flow vein. The heat exchanger extends radially and axially in an upstream section section of the tertiary flow vein, having a divergent longitudinal section, said tertiary flow vein comprises a downstream section presenting a converging longitudinal section, following the tertiary flow.
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
4.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
An axial turbomachine including a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary f flow and a tertiary flow, said tertiary flow being in a tertiary flow vein radially external to said flow primary; and an air/oil type heat exchanger disposed in the tertiary flow stream and including heat exchange surfaces with air and oil passages extending in said tertiary flow stream; and structural arms extending radially through the tertiary flow vein. Each structural arm has in the tertiary flow vein a cross section with a downstream portion having a width decreasing towards the downstream, the heat exchanger being adjacent to said downstream portions of the structural arms.
Disclosed is an axial turbomachine (2) that comprises: a first splitter (10) capable of separating an incoming airflow (F) into a radially internal airflow (F') and a radially external airflow, referred to as secondary flow (F2); a second splitter (14) capable of separating the radially internal airflow into a primary flow (F1) and a tertiary flow (F3), said tertiary flow being in a tertiary stream (16) radially external to said primary flow; an air-to-oil heat exchanger (18) placed in the tertiary stream and including surfaces exchanging heat with the air and oil passages extending into said tertiary stream; and structural arms (60) extending radially through the tertiary stream. The axial turbomachine (2) is characterised in that each structural arm has, in the tertiary stream, a cross-section with a downstream portion (62) the width of which decreases downstream, the heat exchanger being adjacent to said downstream portions of the structural arms.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28D 7/00 - 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
F28D 7/08 - 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 otherwise bent, e.g. in a serpentine or zig-zag
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
Heat exchanger (2) of the air-oil type, for an annular air channel in a turbomachine, comprising a heat exchange zone (3) with oil passages (4) and heat exchange surfaces for heat exchange with air, said heat exchange zone forming an axial air passage and having a profile facing the air flow and contained in a plane perpendicular to the air flow, the profile of the heat exchange zone being in the form of a circular arc such that it can be placed in the annular air channel. The heat exchanger is characterised in that it comprises an oil inlet (18) and an oil outlet (20) on a radially inner (14') or radially outer (16') face of the heat exchange zone, the oil passages comprising several paths (22) between the oil inlet and oil outlet, distributed along the circular arc profile of the heat exchange zone.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F28D 7/00 - 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
F28D 7/08 - 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 otherwise bent, e.g. in a serpentine or zig-zag
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
7.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
The invention relates to an axial turbomachine (2), comprising: a first splitter (10) able to separate an incoming air flow (F) into a radially internal air flow (F') and into a radially external air flow, termed secondary flow (F2); a second splitter (14) able to separate the radially internal air flow into a primary flow (F1) and into a tertiary flow (F3) in a tertiary flow duct (16) radially to the outside of the primary flow; and a heat exchanger (18) arranged in the tertiary flow duct; characterized in that the heat exchanger extends radially and axially in an upstream portion (20) of the tertiary flow duct, having a divergent longitudinal section, the tertiary flow duct comprising a downstream portion (22) having a convergent longitudinal section, along the tertiary flow.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28D 7/00 - 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
F28D 7/08 - 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 otherwise bent, e.g. in a serpentine or zig-zag
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
8.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
Axial turbomachine, comprising: a first splitter nose which can split an incoming air flow into a radially inner air flow and a radially outer air flow, referred to as the secondary flow; a second splitter nose which can split the radially inner air flow into a primary flow and a tertiary flow (F3), the tertiary flow being in a tertiary flow channel (16) radially external to the primary flow and delimited by an inner wall (13) and an outer wall (11); and a heat exchanger (18) of the air-oil type, disposed in the tertiary flow channel. The turbomachine is characterised in that the heat exchanger comprises several angular sectors (38), each angular sector comprising an oil inlet (48) on the inner wall at an angular end of said sector, and an oil outlet (50) on the inner wall at an opposite angular end of said sector.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28D 7/00 - 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
F28D 7/08 - 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 otherwise bent, e.g. in a serpentine or zig-zag
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
9.
AIR-OIL HEAT EXCHANGER COMPRISING A BYPASS FOR A TURBOMACHINE
Heat exchanger (2) for an annular air channel in an axial turbomachine, comprising a heat exchange zone (3) with oil passages (4) and heat exchange surfaces (6) forming a heat exchange passage for air, said heat exchange zone being radially delimited by an upper wall (12) and a lower wall (9), the oil passages extending radially and axially between said upper and lower walls, said heat exchange zone having a profile facing the air flow and contained in a plane perpendicular to the air flow, and the profile of the heat exchange zone being in the form of a circular arc such that it can be placed in the annular air channel. The heat exchanger is characterised in that it further comprises a wall (8) having a circular arc profile and being parallel to, and radially away from, the heat exchange zone so as to form a bypass passage (10) for the air, parallel to the heat exchange passage, between said wall and the heat exchange zone.
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F28D 7/00 - 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
F28D 7/08 - 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 otherwise bent, e.g. in a serpentine or zig-zag
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
A device for detecting particles in a lubricating oil of a machine, comprising a particle separator; at least one particle detector; a bypass conduit for the particle-concentrating oil, fluidly connected to an oil outlet of the particle separator, concentrating the particles; and wherein the at least one particle detector is operatively mounted on the bypass conduit so as to be able to detect particles in the bypass conduit.
The invention relates to an oil deaerator device (2) for a turbomachine lubricating system, comprising a reservoir (4) comprising an internal volume (10) with a bottom (10.1), an oil outlet (18) on the bottom (10.1), and an oil inlet opposite to the bottom (10.1); an oil deaerator (6) arranged at the oil inlet of the reservoir (4); and a stabilizing wall (14) arranged in the internal volume (10) opposite the bottom (10.1) and provided with at least one passage (14.1) for the oil so as to delimit a stabilized buffer oil volume (12).
A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.
A turbomachine compressor module, comprising an annular array of structural arms defining inter-arm spaces between two circumferentially adjacent arms; and an annular array of stator vanes with variable orientation about a respective axis (A) and disposed at least partially within the inter-arm spaces. The arms are provided with flaps pivotable about a respective axis (B). Also, a turbomachine provided with such a module and a row of rotor blades directly downstream of the module.
The invention relates to a turbine engine (1) comprising an unshrouded propeller (14) propelling a tertiary flow (13), a fan (12), a compressor (4) compressing a primary flow (F1), and an annular passage (19) for the flow of a secondary flow (F2) downstream of the fan (12); the annular passage (19) accommodating an annular row of rectifier blades (22) and at least one heat exchanger (24) downstream of the row of blades (22); a plurality of diffusion passages being provided upstream of the at least one exchanger (24), each passage being delimited circumferentially by a pressure side and by a suction side of two circumferentially adjacent blades (22) and by at least one fin supported by at least one of the two circumferentially adjacent blades (22).
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
15.
TURBINE ENGINE FOR AN AIRCRAFT WITH HEAT EXCHANGER
The invention relates to a turbine engine comprising a stator blade (22) having a vane (28) extending circumferentially from the pressure face (22.3) and/or from the suction face (22.4). The blade (22) is intended to be positioned downstream of a rotor and in a diffusion channel in order to slow an air flow upstream of a heat exchanger.
The invention relates to a turbomachine (2) of the type having an unducted fan (4), comprising: a splitter (10) separating an air flow (F) into a primary flow (F1) and a secondary flow (F2); a compressor (14) compressing the primary flow (F1); and an air/oil heat exchanger (24); characterized in that the exchanger (24) is positioned in a channel (26) through which there flows a tertiary flow (F3), the tertiary flow (F3) being drawn from the secondary flow (F2) upstream of the exchanger (24) and impinging, downstream of the exchanger (24), at least one annular row of rotor blades (20, 22) of the compressor (14).
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
17.
HEAT EXCHANGE DEVICE AND AIRCRAFT TURBINE ENGINE WITH THE DEVICE
Heat exchange devices for aircraft turbine engines include a heat exchanger and an inlet scoop comprising an air intake configured for supplying the heat exchanger. The air intake of the inlet scoop is divided into several mouthpieces, each defining an air flux supplying the heat exchanger.
Module (60) for attracting and detecting ferromagnetic debris in an oil flow from a turbomachine, the module (60) comprising: a permanent magnet (62); a bar (64), the bottom (66) of which extends radially and is wound around a coil (70). The coil (70) is able to detect the magnetic field generated by the magnet (62) and in particular its variations when a ferromagnetic particle comes into the vicinity of the magnet (62).
A compressor casing for a turbine engine, the casing comprising: a housing comprising a radially inner e surface; an upstream ferrule; and a downstream ferrule; each of the ferrules having a respective inner surface capable of defining an air stream, and each of the ferrules having an outer surface facing the inner surface of the housing, the ferrules being attached to the cantilevered housing and being axially arranged so as to be separated by an axial clearance. Additionally, a turbine engine comprising such a casing and a stage of variable-setting vanes.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
F04D 29/52 - CasingsConnections for working fluid for axial pumps
An internal gear pump comprising: a ring with internal teeth delimiting a cavity and a gear disposed in the cavity, the gear comprising external teeth cooperating with the internal teeth to drive the ring in rotation, remarkable in that it comprises a pinion disposed in the cavity and driving the gear in rotation. The pinion cooperates with the external toothing of the gear. In an alternative embodiment, the gear comprises an internal toothing which cooperates with the pinion.
F04C 2/10 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of internal-axis type with the outer member having more teeth or tooth-equivalents, e.g. rollers, than the inner member
F04C 15/00 - Component parts, details or accessories of machines, pumps or pumping installations, not provided for in groups
F04C 15/06 - Arrangements for admission or discharge of the working fluid, e.g. constructional features of the inlet or outlet
The invention relates to a sandblasting mask (50) and to the use thereof for sandblasting blade tips in a method comprising: a step of positioning a plurality of sandblasting masks (50), each blade passing through an opening (58) in a mask and each blade tip projecting from the respective mask, the masks being assembled in pairs preferably without play; and a step of sandblasting the blade tips projecting from the masks.The masks (50) are preferably produced by additive manufacturing in plastic and covered with a polyurea-based coating.
B24C 1/04 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
B05B 12/24 - Masking elements, i.e. elements defining uncoated areas on an object to be coated made at least partly of flexible material, e.g. sheets of paper or fabric
B23P 5/00 - Setting gems or the like on metal parts, e.g. diamonds on tools
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
B24C 3/32 - Abrasive blasting machines or devicesPlants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks
A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the body of the heat exchanger is of cylindrical shape. The present disclosure also concerns a turbine engine comprising the heat exchanger and a manufacturing method for manufacturing the heat exchanger.
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
A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the first and second fluid have a respective general direction of flow, and the general direction of flow of the first fluid is parallel to the general direction of flow of the second fluid. The present disclosure also concerns a turbine engine comprising the heat exchanger and a manufacturing method for manufacturing the heat exchanger.
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
24.
CART FOR ASSEMBLING AND TRANSPORTING AN AIRCRAFT ENGINE TO A TEST CELL
Disclosed is a cart (2) for transporting an aircraft engine, comprising a base frame (4) equipped with wheels (6) for riding on a floor; at least two engine arms (14, 16) extending horizontally and movable vertically relative to the base frame, structured and designed for supporting the aircraft engine; and at least two adapter arms (20) extending horizontally at a higher level than the at least two engine arms, structured and designed for supporting an adapter coupled at the top of the aircraft engine. Disclosed is also a method of transporting an aircraft engine to a test cell.
The invention relates to a detection device (25) for detecting particles in a lubricating oil of a machine, comprising a particle separator (24.1, 24.5, 24.6); at least one particle detector (25.2, 25.3); a bypass pipe (25.1) for the oil concentrating the particles, which is in fluid communication with an oil outlet (24.7) of the particle separator (24.1, 24.5, 24.6), concentrating the particles; and in which the at least one particle detector (25.2, 25.3) is mounted operationally on the bypass pipe (25.1) so as to be able to detect the particles in the bypass pipe.
The invention relates to a rotar blade (24) for a compressor (4) extending substantially radially and comprising a vane (24.1), the geometry of which is due to the stacking of wing section-shaped profiles in a line (L) called a stacking line, characterised in that the stacking line (L) passes through at least three points including a point (A) forming the blade foot (24), a point (F) defining the blade head (24) and a point (E) forming the radial extremum of the stacking line (L).
The invention relates to a transonic compressor (24) of a turbomachine (2) comprising exactly two or exactly three annular rows of rotor blades (40, 44) and respectively exactly one or exactly two annular row(s) of intermediate stator blades (41) interleaved between two respective rows of rotor blades (40, 44), in which compressor the speed of the flow relative to the rotor (44) downstream of the intermediate stator blades (41) is less than or equal to a Mach number of 0.9 over a radial portion of the blades (44) extending over the radially innermost 40% of the blades (44), and less than or equal to a Mach number of 1 over a radial portion extending over the radially innermost 80% of the blades (44), and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outermost 20% of the blades (44).
The invention relates to a turbomachine compressor module (47), comprising an annular row of structural arms (46) defining inter-arm spaces (56) between two circumferentially adjacent arms (46, 48); and an annular row of stator vanes (39) with variable orientation about an axis (A) and arranged at least partially in the inter-arm spaces (56). The arms (46) are provided with flaps (60) that can be pivoted about an axis (B). The invention also relates to a turbomachine provided with such a module (47) and a row of rotor vanes (40) directly downstream from the module.
The invention relates to a method for manufacturing a compressor blade of a turbomachine, comprising the following steps: determining the residual deformation and/or stresses of the part during and after each operation of the manufacturing process, the operations comprising a forging operation and optionally one of the following operations: burr removal, cooling and/or heat treatment; integration of the residual deformation and/or stresses thus determined for the parameterisation of the forging operation, in particular as a function of a comparison between the determined residual deformation and/or stresses and a nominal residual deformation and/or stresses; and carrying out the forging operation thus parameterised. The invention also relates to a compressor comprising a blade produced at least in part by the manufacturing method of the invention.
B21K 3/04 - Making engine or like machine parts not covered by Making propellers or the like blades, e.g. for turbinesUpsetting of blade roots
G06F 30/23 - Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
30.
Compressor casing with oil tank for a turbine engine
Turbine engine assembly comprising: an external casing (28) of a low-pressure compressor (4), an annular wall (30) and an oil tank (46) with a circular chamber (48) around an axis (14) of the compressor. The wall (30) comprises an inner surface (38) delimiting an primary guide path for the flow of the compressor, and an external surface (40) radially opposite the inner surface and delimiting the internal chamber (48) of the tank (46).
System (45) for detecting ferromagnetic debris in an oil stream (F1, F2), the system comprising a passage (50) through which the stream (F1, F2) is intended to flow and a module (60) for detecting the ferromagnetic debris present in the stream (F1, F2), the detection module (60) comprising: a permanent magnet (66); and a coil (72) suitable for detecting the magnetic field (68) generated by the magnet; characterised in that the detection module (60) is arranged in the passage (50) and the detection module (60) further comprises a casing (62) which is sealed off from the stream (F1, F2) and in which the magnet (66) and the coil (72) are confined.
G01N 15/06 - Investigating concentration of particle suspensions
G01N 27/83 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws by investigating stray magnetic fields
32.
Assembly for axial turbomachine, associated axial turbomachine, assembly method, and sealing joint
Assembly for axial turbomachine, in particular for an aircraft turbojet, the assembly comprising: an annular casing with an internal surface (40); an annular row of stator baffles (26) with at least one stator baffle (26) comprising an airfoil (50) which extends radially from a fixing platform (34), the fixing platform (34) being fixed to the casing and having a polygonal outline; characterised in that it further comprises a gasket (80) comprising a frame, the outline of which conforms to the polygonal outline of the fixing platform (34), the frame being in radial contact with the fixing platform (34) and the casing in order to ensure a seal.
A fluid valve for a hydraulic circuit of an aircraft includes a valve body with an inlet and two outlets. The valve further includes a solenoid electric actuator with a ferromagnetic mobile driver and a valve member having a ferromagnetic portion/ The valve member is movable within the valve body along a main direction and has first and second ends that define first and second cavities, respectively, on opposite sides of the valve member. A longitudinal cavity extends through the valve member parallel to the main direction and opens into the second cavity. Relative displacement between the mobile driver and the valve member modifies a communication between the longitudinal cavity and the first cavity via a side opening that is perpendicular to the main direction.
F16K 31/42 - Operating meansReleasing devices actuated by fluid by means of electrically-actuated members in the supply or discharge conduits of the fluid motor
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
F16K 31/122 - Operating meansReleasing devices actuated by fluid the fluid acting on a piston
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
Internal-gear pump (10) comprising: a ring gear (14) with an internal toothing (14.1) delimiting a cavity (15) and a toothed wheel (12) disposed in the cavity (15), the toothed wheel (12) comprising an external toothing (12.1) that cooperates with the internal toothing (14.1) in order to drive the ring gear (14) in rotation. A pinion (18) disposed in said cavity (15) drives the toothed wheel (12) in rotation and cooperates with the external toothing (12.1) of the toothed wheel (12). In an alternative embodiment, the toothed wheel comprises an internal toothing that cooperates with the pinion.
F04C 2/10 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of internal-axis type with the outer member having more teeth or tooth-equivalents, e.g. rollers, than the inner member
F04C 15/00 - Component parts, details or accessories of machines, pumps or pumping installations, not provided for in groups
F04C 15/06 - Arrangements for admission or discharge of the working fluid, e.g. constructional features of the inlet or outlet
The invention relates to a turbine engine (2) compressor shroud, comprising: first and second sections (130, 230) and respective flanges (131, 231), the flanges (131, 231) making it possible to hold the two sections (130, 230) together, the first section (130) comprising a cylindrical surface (137) forming a seat for an actuating device (136, 140, 166, 168, 170) for orienting stator blades (126), characterised in that the first shroud (130) comprises a tubular wall (132) axially overlapping both flanges (131, 231) and said cylindrical surface (137) is an outer surface of the tubular wall (132). The invention also relates to an assembly with the shroud (130, 230), the blade (126) and means (140) for actuating the orientation of the blade (126), the shroud being produced using the kit described above. The invention finally relates to a method for assembling a compressor with such an assembly.
Compressor casing (50) for a turbine engine, the casing (50) comprising: - a housing (52) comprising a radially inner surface (52.1); - an upstream ferrule (54); and - a downstream ferrule (56); each of the ferrules (54, 56) having a respective inner surface (54.5, 56.5) capable of defining an air stream (18), and each of the ferrules (54, 56) having an outer surface (54.1, 56.1) facing the inner surface (52.1) of the housing (52), the ferrules (54, 56) being attached to the cantilevered housing and being axially arranged so as to be separated by an axial clearance (58). The invention also relates to a turbine engine comprising such a casing and a stage (76) of variable-setting vanes (78).
A turbojet engine (2), such as an aircraft turbojet engine, comprising: an epicyclic gear train (36); a turbine rotating a transmission shaft (34) constrained to rotate with the inner planetary gear (60) of the epicyclic gear train (36); a fan (18) rigidly connected to the ring gear (66) of the epicyclic gear train (36); and an electric machine (70) comprising a rotor (72) and a stator (74), the rotor (72) being rigidly connected to the planet carrier (68) of the epicyclic gear train (36). Alternatively, the fan (18) is rigidly connected to the planet carrier and the electric machine (70) is rigidly connected to the ring gear. The invention also relates to methods for using said turbojet engine, in particular for controlling the reduction ratio between the transmission shaft and the turbine, in order to recover kinetic energy or for taxiing.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
F02C 3/067 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
38.
Passive fluidic valve for fixed flow rate distribution
A passive fluidic valve for fixed flow rate distribution comprising: a hollow valve body; a valve member for blocking a passage to one of the two outlets; and communications to impose the pressure of the upstream and downstream cavities at the ends of the valve member. The valve body further comprises: an inlet; a first outlet comprising a first restriction delimiting an upstream cavity and a downstream cavity; a second outlet comprising a second restriction delimiting an upstream cavity and a downstream cavity; and a first and a second cavity. The valve member further comprises: a first end in the first cavity delimiting a first and a third chambers, and a second end in the second cavity delimiting a second and a fourth chambers.
F15B 13/02 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors
G05D 11/03 - Controlling ratio of two or more flows of fluid or fluent material without auxiliary power
B64C 13/00 - Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
F16K 11/065 - 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
F16K 27/04 - Construction of housingsUse of materials therefor of sliding valves
The invention relates to a method for handling a rectifier of a turbojet of an aircraft, the rectifier having an axis defining the asymmetry thereof, said method comprising a step of placing the rectifier on the rollers of a supporting structure, the structure and the rollers thereof being arranged such that the axis of the rectifier is inclined at a non-null acute angle in relation to the horizontal, and a step of controlling, maintaining, assembling, handling, storing, deburring and/or cleaning the rectifier, during which the rectifier is pivoted about the axis thereof. The invention also relates to a trolley for handling a rectifier for an axial turbojet, said trolley comprising at least two of the lower rollers that have axes inclined in relation to the horizontal of said angle and at least one upper roller, the axis of which is inclined in relation to the vertical of said angle.
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
B23K 37/053 - Auxiliary devices or processes, not specially adapted for a procedure covered by only one of the other main groups of this subclass for holding or positioning work aligning cylindrical workClamping devices therefor
B66F 5/00 - Mobile jacks of the garage type mounted on wheels or rollers
B62B 3/10 - Hand carts having more than one axis carrying transport wheelsSteering devices thereforEquipment therefor characterised by supports specially adapted to objects of definite shape
A heat exchanger includes a plurality of fins arranged as a network and delimiting corridors, and an envelope having an internal wall and an external wall, the internal and external walls delimiting between them a channel for a flow of a first fluid in a main direction, the network of fins being arranged in the channel and connected to the internal and external walls, at least one passage for a flow of a second fluid being embedded in at least one of the internal and external walls, the channel being, in the main direction, divergent and then convergent.
F28D 1/02 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid
F28D 7/00 - 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
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
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
F28D 9/02 - 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 heat-exchange media travelling at an angle to one another
F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
F02C 7/14 - Cooling of plants of fluids in the plant
A method of testing and/or controlling the operation of an axial turbomachine through which passes a gas stream, includes the following actions: measurement of operating parameters of the turbomachine, said parameters including pressure in the gas stream at different axial positions, and calculation of operating conditions of the turbomachine from the measured parameters and the Laplace coefficient γ of the gas passing through the turbomachine, wherein the measurement of parameters includes a measurement of the temperature of the gas stream, and the calculation of operating conditions includes a determination of the Laplace coefficient γ on the basis of the measurement of the temperature of the gas stream.
A rotor for an axial turbomachine includes a drum formed of several parts including: composite rings made of composite material and metallic rings interposed between the composite rings. The metallic rings carry the rotor blades. The metallic rings have an axial branch axially overlapping the composite rings and at least one radial branch in contact with the composite rings.
The invention relates to a tank (32) for liquid, in particular of a turbine engine such as an aircraft turbojet engine, the tank comprising an external wall (36) with an inner surface (48); an inner chamber intended for containing the liquid of the tank (32) and defined by the inner surface of the external wall; and a system (42) for measuring the level of liquid. The system comprises: a submersible portion matching the inner surface of the wall (36); a clearance (52) separating the submersible portion from the inner surface; and a liquid detector (54) configured to emit a signal towards the submersible portion through the clearance, said signal being configured to be modified in the event that liquid is present in the clearance (52). The invention likewise relates to a method for measuring a level of liquid, and an associated computer program.
A matrix for exchanging heat between a first fluid and a second fluid, in particular for an air-oil application in a turbine engine, includes an envelope defining a flow path of the first fluid and a network extending into the flow path and in which the second fluid flows. Along the axis defined by the curvature of the matrix, the dimensions of the envelope vary circumferentially (T(A)) and radially (R(A)). The matrix may be used with a heat exchanger.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02C 7/14 - Cooling of plants of fluids in the plant
B33Y 80/00 - Products made by additive manufacturing
F28D 1/02 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid
F28F 7/02 - Blocks traversed by passages for heat-exchange media
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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
A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the meshes are stacked in staggered rows.
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
System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydraulic circuit (40) form a single and common oil circuit and the oil circuit comprises a pump (50) with a heating element integrated in the pump for heating the oil.
The pump may be an electric pump with an electric motor, wherein the electric motor comprises a coil fed with DC current forming a heating element for heating the oil.
The pump may comprise a body and the heating element may be an electric resistor embedded into the body of the pump and in direct contact with the oil.
The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.
F02B 77/08 - Safety, indicating, or supervising devices
G01L 19/00 - Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
G01L 7/08 - Measuring the steady or quasi-steady pressure of a fluid or a fluent solid material by mechanical or fluid pressure-sensitive elements in the form of elastically-deformable gauges of the flexible-diaphragm type
The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface (40) and two hydrophobic surfaces (42; 44) which extend the ice-phobic surface (40) on the pressure side (32) and the suction side (34) to allow water droplets escaping from the leading edge (28) to flow.
A turbine engine compressor blade includes a leading edge, a trailing edge, a suction surface, and a pressure surface. In addition, the blade includes at least one irregularity in the form of a projecting protuberance of the suction surface or the pressure surface or in the form of a recess nested in the suction surface or the pressure surface. The irregularity may have a direction of longest dimension substantially parallel to the leading edge or substantially axial.
The invention relates to a turbine engine (2) compressor shroud, comprising: first and second sections (130, 230) and respective flanges (131, 231), the flanges (131, 231) making it possible to hold the two sections (130, 230) together, the first section (130) comprising a cylindrical surface (137) forming a seat for an actuating device (136, 140, 166, 168, 170) for orienting stator blades (126), characterised in that the first shroud (130) comprises a tubular wall (132) axially overlapping both flanges (131, 231) and said cylindrical surface (137) is an outer surface of the tubular wall (132). The invention also relates to an assembly with the shroud (130, 230), the blade (126) and means (140) for actuating the orientation of the blade (126), the shroud being produced using the kit described above. The invention finally relates to a method for assembling a compressor with such an assembly.
The invention relates to a turbojet engine (2), such as an aircraft turbojet engine, comprising: an epicyclic gear train (36); a turbine rotating a transmission shaft (34) constrained to rotate with the inner planetary gear (60) of the epicyclic gear train (36); a fan (18) rigidly connected to the ring gear (66) of the epicyclic gear train (36); and an electric machine (70) comprising a rotor (72) and a stator (74), the rotor (72) being rigidly connected to the planet carrier (68) of the epicyclic gear train (36). Alternatively, the fan (18) is rigidly connected to the planet carrier and the electric machine (70) is rigidly connected to the ring gear. The invention also relates to methods for using said turbojet engine, in particular for controlling the reduction ratio between the transmission shaft and the turbine, in order to recover kinetic energy or for taxiing.
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
F02C 3/067 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
52.
CASING WITH A CHANGING PROFILING FOR A TURBOMACHINE COMPRESSOR
The invention relates to a low-pressure compressor of an axial turbomachine such as a turbojet. The compressor comprises a row of blades (34) extending radially from an annular surface (42) in a non-axisymmetric form, known as 3D contouring. In the inter-blade passages (44), the annular surface (42) comprises an arched row of bumps (56) offset in relation to the inter-blade pitch, each one having a maximum height (H); and an arched row of cavities (62) offset in relation to the inter-blade pitch, each one having a maximum depth (P). The maximum heights (H) and the maximum depths (P) vary according to the circumference of the annular surface (42) such that the profiling changes around the compressor. The invention also relates to a casing or a casing segment and a turbomachine.
The invention relates to a system for an aircraft, comprising: a turbojet engine (2) equipped with a hydraulic lubrication circuit (30); and/or a fuel cell (28) equipped with a hydraulic circuit (40) for reaching and maintaining the operating temperature. The system of the invention is characterised in that at least one of the circuits (30, 40) comprises an electric circulation pump (50) incorporating a heating element for heating the oil. The heating element can in particular be a heating module or the DC-powered coil of the pump, in thermal contact with the oil. The invention also relates to an air/oil heat exchanger for such a system. The exchanger comprises a matrix produced by means of additive manufacturing.
F01D 25/20 - Lubricating arrangements using lubrication pumps
F02C 6/10 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
The invention relates to a tank (32) for liquid, in particular of a turbine engine such as an aircraft turbojet engine, the tank comprising an external partition (36) with an inner surface (48); an inner chamber intended for containing the liquid of the tank (32) and defined by the inner surface of the external partition; and a system (42) for measuring the level of liquid. The system comprises: a submersible portion matching the inner surface of the partition (36); a clearance (52) separating the submersible portion from the inner surface; and a liquid detector (54) configured to emit a signal towards the submersible portion through the clearance, said signal being configured to be modified in the event that liquid is present in the clearance (52). The invention likewise relates to a method for measuring a level of liquid, and an associated computer program.
The invention relates to a method for handling a rectifier of a turbojet of an aircraft, the rectifier having an axis defining the asymmetry thereof, said method comprising a step of placing the rectifier on the rollers of a supporting structure, the structure and the rollers thereof being arranged such that the axis of the rectifier is inclined at a non-null acute angle in relation to the horizontal, and a step of controlling, maintaining, assembling, handling, storing, deburring and/or cleaning the rectifier, during which the rectifier is pivoted about the axis thereof. The invention also relates to a trolley for handling a rectifier for an axial turbojet, said trolley comprising at least two of the lower rollers that have axes inclined in relation to the horizontal of said angle and at least one upper roller, the axis of which is inclined in relation to the vertical of said angle.
The invention relates to an axial turbomachine, in particular a turbofan for an aircraft. The turbomachine comprising a compressor, also referred to as a booster, with a rotor (12) and a stator, a turbine, a combustion chamber axially between the compressor and the turbine, and a rotary electric machine (30) coupled in rotation with the turbine and the compressor. The rotary electric machine (30) is of the axial flux type and comprises windings (38) and magnets (40) that receive and produce axial magnetic flux. The invention further proposes a method for compressing a fluid in a turbomachine where the compressor is equipped with an axial-flux rotary electric machine (30) for the purpose of producing electricity and rotating the compressor.
Shroud assembly of an axial turbomachine (2) having a rotor (12), such as a turbomachine compressor air-intake shroud (28). The assembly comprises an annular layer (32) of abradable material that is able to cooperate by abrasion with lips (44) of the turbomachine in order to ensure tightness, and a heating module (38) for the abradable layer (32). The module (38) comprises electrical heating resistors (42) within the abradable material in order to prevent the presence of ice on the shroud (28). The abradable material is thus used as a heating body which receives, transports and distributes the heat used for de-icing.
F01D 25/02 - De-icing means for engines having icing phenomena
F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
The invention relates to a fluid valve (50) for a hydraulic circuit of an aircraft, comprising: - a valve body (20) comprising one inlet (22), two outlets (23); - a solenoid electric actuator (40) comprising a ferromagnetic mobile driver (41); - said valve member (5) having a portion comprising a ferromagnetic material: - comprising first (51) and second (52) ends, - defining first (1) and second (2) cavities located on either side of the valve member (5) and comprising a longitudinal cavity (46) extending parallel to a main direction (100) and leading into said second cavity (2), such that a relative movement between the mobile controller (41) and the valve member (5) makes it possible to modify a communication between the longitudinal cavity (46) and the first cavity (1) via a side opening (101) perpendicular to the main direction (100).
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
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
F16K 31/122 - Operating meansReleasing devices actuated by fluid the fluid acting on a piston
F16K 31/40 - Operating meansReleasing devices actuated by fluid in which fluid from the conduit is constantly supplied to the fluid motor with electrically-actuated member in the discharge of the motor
A structural casing for an axial turbine engine includes an outer ring, an inner hub, and a plurality of struts extending radially from the hub to the ring, wherein the ring is made of a plurality of angular segments welded together. The segments extend circumferentially of different angles, some segments being larger angularly than others. The structural casing is adapted to be an intermediate casing between two compressors of a turbine engine.
A turbomachine assembly and, in particular, a low-pressure compressor of an aircraft turbojet engine includes an annular row of upstream vanes with trailing edges extending radially from an upstream support; an annular row of downstream vanes with leading edges axially facing the trailing edges and extending radially from a downstream support; an annular passageway delimited by the upstream support and the downstream support. The downstream support has a profile with: an upstream portion delimiting the annular passageway forming an annular slide, a downstream portion axially at the level of downstream vanes, and a connecting arc connecting the upstream portion to the downstream portion. The connecting arc is arranged downstream of the leading edges.
F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
F01D 5/08 - Heating, heat-insulating, or cooling means
F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
F01D 5/06 - Rotors for more than one axial stage, e.g. of drum or multiple-disc typeDetails thereof, e.g. shafts, shaft connections
F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
61.
Matrix for an air/oil heat exchanger of a jet engine
Matrix (30) for a heat exchanger to exchange heat between a first fluid and a second fluid, the first fluid being for instance air and the second fluid being for instance oil. The matrix (30) comprises: a channel for the first fluid. an array of passages for the second fluid, the passages extending in the channel. The array supports at least two cooling fins. The matrix is made by a process of additive manufacturing. The fins are inclined with respect to each other along the direction of the flow of the first fluid.
F28F 1/10 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
F28F 1/12 - 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
F28F 1/38 - 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 being staggered to form tortuous fluid passages
F28F 1/34 - 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 obliquely
F28D 7/16 - 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 in parallel spaced relation
Assembly for axial turbomachine, in particular for an aircraft turbojet, the assembly comprising: an annular casing with an internal surface (40); an annular row of stator baffles (26) with at least one stator baffle (26) comprising an airfoil (50) which extends radially from a fixing platform (34), the fixing platform (34) being fixed to the casing and having a polygonal contour; characterised in that it further comprises a sealing joint (80) comprising a frame, the contour of which conforms to the polygonal contour of the fixing platform (34), the frame being in radial contact with the fixing platform (34) and the casing in order to ensure a seal.
In an axial turbomachine low-pressure compressor, the compressor, or booster, includes a first vane with an intrados surface, a second vane with an extrados surface, an inter-vane passage with a guiding surface, which connects the intrados surface to the extrados surface delimiting an annular vein, and which has a bulge and a recess forming a so-called 3D contouring geometry, or non-axisymmetric surface. The guiding surface includes an axially symmetrical or substantially flat zone, which axially extends through the inter-vane passage so as to separate the recess from the bulge.
A low-pressure compressor for an axial-flow turbomachine, such as a jet engine, includes an annular row of vanes and a between-vanes passage with a connecting surface that links the pressure surface of a first vane to the suction surface of a second vane of the row. The connecting surface includes a main protuberance which includes a first elevation and a second elevation that are spaced apart from one another.
A compressor for a turbine engine includes an annular row of blades including a first blade with an extrados surface and a second blade with an intrados surface; and a connecting surface joining the intrados surface to the extrados surface, the connecting surface having a bulge of volume VB and a recess of volume VC, the bulge and recess forming a contouring 3D. The volume of the bulge VB is greater than four times the volume VC of the recess, the connecting surface includes a flat or axisymmetric band circumferentially separating the bulge from the recess, and the bottom of the recess being formed against the intrados surface.
The invention relates to an assembly for a turbine engine, comprising: an external housing (28) for a low-pressure compressor (4), referred to as a booster, having an annular wall (30); and an oil tank (46) having a circular internal chamber (48) around the axis of rotation (14) of the compressor. The wall (30) has an internal circular surface (38) defining the primary flow path of the compressor, and an external circular surface (40) radially opposite and defining the internal chamber (48) of the tank (46). The invention also proposes several arrangements of tanks with respect to the rows of blades (24; 26).
A method for manufacturing a curved composite casing for a turbomachine, notably for a low-pressure compressor of an aircraft turbojet engine, includes the following sequence of steps: (a) draping a preform by automatic placement of carbon fibres on a concave form, referred to as a female form; (b) laying a glass-fibre ply on a convex form, referred to as a male form; (c) transferring the preform onto the convex form, covering the glass-fibre ply on the convex form. Step (b) laying includes a phase (α) of laying a metal strip and/or an epoxy profile on the convex form, then a phase (β) of covering the metal strip with the glass-fibre ply.
B29C 70/84 - Moulding material on preformed parts to be joined
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
B29C 70/78 - Moulding material on one side only of the preformed part
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B29K 705/00 - Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
68.
TURBOMACHINE LUBRICATION UNIT AND METHOD OF MANUFACTURE
The invention relates to an aircraft bypass turbojet engine lubrication unit. The lubrication unit comprises from three to five superposed pumps, a body housing the pumps and which has an internal passage (58) communicating with each of the pumps. The material of the body exhibits a stack of layers (40) in a direction of stacking (44), the pumps being housed in the said stack of layers (40). The passage (58) exhibits an end (86) in the direction of stacking (44) of the layers and an internal profile (78), for example triangular, with two straight lines which form the said end and which are inclined with respect to the stacked layers. The invention also proposes the production of a lubrication unit by additive manufacturing in layers.
An aircraft bypass turbojet engine lubrication unit includes from three to five superposed pumps, a body housing the pumps and which has an internal passage communicating with each of the pumps. The material of the body exhibits a stack of layers in a direction of stacking, the pumps being housed in the said stack of layers. The passage exhibits an end in the direction of stacking of the layers and an internal profile, for example triangular, with two straight lines which form the said end and which are inclined with respect to the stacked layers. The production of a lubrication unit includes additive manufacturing in layers.
An aircraft bypass turbojet engine lubrication unit includes from three to five superposed pumps, a body housing the pumps and an internal passage in the body for communicating with each of the pumps. The material of the body exhibits a stack of layers in a direction of stacking, the pumps being housed in the said stack of layers. The passage exhibits an end in the direction of stacking of the layers and an internal profile, for example triangular, with two straight lines which form the said end and which are inclined with respect to the stacked layers. The lubrication unit may be manufactured by additive manufacturing in layers.
F01D 25/20 - Lubricating arrangements using lubrication pumps
B22F 5/10 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
The invention relates to a system of vanes with adjustable orientation, also called a system of variable stator vanes, for a low-pressure compressor of an axial turbine engine. The system comprises vanes, each having a vane extending radially in a flow of the turbine engine and a spindle having a cylindrical portion connected to a telescopic actuating lever. The cylindrical portion comprises radially extending slot, and the actuating lever comprises a pivot joint housed in the slot, that is configured to communicate a rotary movement to the vane about its spindle. The invention also proposes a compressor and a turbine engine.
A low-pressure compressor for a turbine engine, such as an aircraft turbojet engine includes a rotor with two rows of rotor blades between which two annular ribs are positioned; and one annular row of stator blades between the rotor blades. An internal shroud is connected to the stator blades. The internal shroud includes abradable material collaborating with the annular ribs, and annular teeth made of an abradable material and which extend radially towards the rotor, so as to provide sealing. The system may be used in a method for manufacturing a bypass turbojet engine compressor.
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
An aircraft turbojet engine low-pressure compressor or booster, comprising an inlet structure de-iced by a pressurized hot fluid circulation coming from the high-pressure compressor. The de-icing structure comprises a deformable membrane through the thickness of which the pressurized fluid circulation passes. When there is a build-up of ice on the membrane, the pressurized fluid circulation is blocked, resulting in its pressure deforming the membrane in such a manner as to crack the build-up of ice.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
F01D 25/02 - De-icing means for engines having icing phenomena
A system for measuring turbulence of a flow of a turbine engine, notably of a turbine engine compressor includes a first housing with a first pressure sensor and a first inlet, a second housing with a second pressure sensor and a second inlet inclined relative to the first inlet, and a temperature sensor. The system is configured to calculate at least two orientation components of the velocity of the flow on the basis of the pressure sensors and the temperature sensor. The inlets are disposed at the vane foot, on the leading edge at the level of an internal shell.
An oil tank of a turbine engine, particularly of an aircraft turbojet includes an external wall forming a generally curved main cavity. This cavity includes an arched sensor for electrically measuring the oil level, for example in a capacitive manner. Said arched sensor matches the curvature of the main cavity in order to be integrated therein. Sensor supporting arms distributed along the curvature of the arched sensor and/or an arched sleeve with an arched cavity receive the arched sensor. A turbine engine is provided with an oil tank, as well as a method for mounting a sensor in an oil tank.
G01F 23/22 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water
G01F 23/26 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields
F16N 19/00 - Lubricant containers for use in lubricators or lubrication systems
G01F 23/00 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
G01F 23/24 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of resistance of resistors due to contact with conductor fluid
76.
TURBINE ENGINE COMPRESSOR WITH A TURBULENCE SENSOR
A system for measuring turbulence of a flow of a turbine engine, notably of a turbine engine compressor has: a first housing with a first pressure sensor and a first inlet; a second housing with a second pressure sensor and a second inlet inclined relative to the first inlet, and a temperature sensor. The system is configured to calculate at least two orientation components of the velocity of the flow on the basis of the pressure sensors and the temperature sensor. The inlets are disposed at the vane foot, on the leading edge at the level of an internal shell.
A turbine engine casing, and in particular an axial turbine engine compressor casing, includes an annular wall and a fastening flange associated with the wall. The fastening flange includes a fastening surface applied against a corresponding mounting surface of the turbine engine, for example, a surface on an intermediate fan casing or a mounting surface of a flow separator. The fastening flange includes at least one electrical connector with one end lying flush with the fastening surface of said fastening flange.
An aircraft turbojet low-pressure compressor includes a sealing device for a turbine engine. The device includes an internal stator shroud connected to an external casing via an annular row of stator vanes and a rotor with two brush seals arranged inside the shroud and respectively upstream and downstream. The internal shroud includes a frustoconial internal surface, which is associated with each brush seal. Each frustoconical surface lies flush with and is inclined with respect to the bristles of the brush seal, so as to seal with the said brush. A method for assembling a sealing device is also proposed.
A jet engine includes an external cowling, a member such as an oil reservoir, and a monitoring system for the member that is able to determine information relating to the member. The external cowling includes a visualization screen that is able to communicate with the monitoring system or directly with the member, so as to display the information specific to the member. When installed in the nacelle of the jet engine, this cowling becomes a smart cowling. The system also includes a method for inspecting a member of an aircraft jet engine and a corresponding computer program.
G07C 5/00 - Registering or indicating the working of vehicles
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A spark erosion machine includes a frame with a space for spark erosion of a workpiece, a wire for cutting by spark erosion, and a wire guide head for guiding the wire across the workpiece, so as to detach an offcut from it; an offcut support mounted movably relative to the guide head, the support being configured to move at least between a retention position under the spark erosion space, where it can collect the offcut, and a retracted position; and an offcut extractor.
B23H 7/26 - Apparatus for moving or positioning electrode relatively to workpieceMounting of electrode
B23H 1/02 - Electric circuits specially adapted therefor, e.g. power supply, control, preventing short circuits or other abnormal discharges
B23H 11/00 - Auxiliary apparatus or details, not otherwise provided for
B23H 9/00 - Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
F04C 2/08 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
F04C 2/10 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of internal-axis type with the outer member having more teeth or tooth-equivalents, e.g. rollers, than the inner member
An assembly for a turbojet, wherein the assembly includes an outer shroud and an inner shroud that are concentric, wherein the inner shroud is segmented and includes circumferential clearances between the segments thereof. The assembly additionally includes an annular row of stator vanes connecting the inner shroud to the outer shroud, a drive with a reduction ratio that is intended to be coupled to a fan, and a circuit for cooling and for lubricating the drive. The circuit is configured to heat up at least the outer shroud during the operation of the turbine engine such as to circumferentially reduce the circumferential clearances between the segments.
The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface (40) and two hydrophobic surfaces (42; 44) which extend the ice-phobic surface (40) on the pressure side (32) and the suction side (34) to allow water droplets escaping from the leading edge (28) to flow.
The invention relates to an assembly for a shroud (28) of an axial turbomachine having a rotor (12), such as a turbomachine compressor air-intake shroud (28). The assembly comprises an annular layer (32) of abradable material that is able to cooperate by abrasion with lips (44) of the turbomachine in order to ensure tightness, and a heating module (38) for the abradable layer (32). The module (38) comprises electrical heating resistors (42) in the abradable material in order to prevent the presence of ice on the shroud (28). The abradable material is thus used as a heating body which receives, transports and distributes the heat used for de-icing.
F04D 29/52 - CasingsConnections for working fluid for axial pumps
F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
F01D 25/02 - De-icing means for engines having icing phenomena
The invention relates to a de-icing splitter nose (22) of an axial turbine engine, notably a de-icing splitter nose of a turbo-jet engine compressor. The splitter nose includes an annular row of vanes (26), each of which has a radially extending leading edge (36), and a de-icing system (28) based on hot-air injection. The injection is pulsed, i.e. discontinuous. The system (28) includes an annular row of injection orifices for injecting de-icing fluid (44) onto the vanes (26) in respective injection directions (46). Each injection orifice is associated with a vane such that the injection directions thereof are substantially parallel to the leading edge (36) of the related vane, enabling said vane (26) to be de-iced.
F01D 25/02 - De-icing means for engines having icing phenomena
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
85.
Additive manufacturing method for a turbofan engine oil tank
The invention relates to a method of manufacturing at least one tank with a shell, in particular a turbojet engine oil tank. The method comprises the following stages: (a) definition of different shell sections (58) for each tank, whereof a first shell section (58) has a recess (60) and a second shell section (58) a boss (62); (b) production of the shell sections (58) by additive manufacturing in which the boss (62) on the second shell section is produced in the recess (60) in the first shell section; then (c) welding of the sections (60) one to the other.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools
B22F 5/10 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
B33Y 80/00 - Products made by additive manufacturing
B29C 64/147 - Processes of additive manufacturing using only solid materials using sheet material, e.g. laminated object manufacturing [LOM] or laminating sheet material precut to local cross sections of the 3D object
B22F 7/04 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers with one or more layers not made from powder, e.g. made from solid metal
F16N 19/00 - Lubricant containers for use in lubricators or lubrication systems
B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
C22C 1/04 - Making non-ferrous alloys by powder metallurgy
A turbojet engine oil tank includes a main chamber and an envelope delimiting the main chamber, and a fixing portion for example with fixing flanges and a branch. The envelope features in particular an envelope part relative to which the fixing portion projects. The envelope part and the fixing portion are produced by layered additive fabrication so as to be in one piece. A method of fabricating an oil tank includes steps of designing an oil tank with a main chamber, an envelope delimiting the main chamber, and a fixing portion; the envelope comprising a part from which the fixing portion projects outwards; and layered additive fabrication of the envelope part and of the fixing portion so as to be one-piece.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
The invention relates to a method for replacing an aircraft part; in particular an aircraft turbine engine; the method comprising the following steps: (a) deciding (100) to replace a part, in particular a faulty part; (b) landing (102) the aircraft in an airport; (c) additive manufacturing (104) of the replacement part at said airport; (d) certifying (106) the replacement part produced during the additive manufacturing step (c); (e) replacing (108) the faulty part with a replacement part certified compliant; and (f) taking off (110) in the aircraft with the new replacement part. The invention also proposes a method for certifying a replacement part obtained through an additive manufacturing method.
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
B22F 3/00 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sinteringApparatus specially adapted therefor
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
B29C 73/00 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass
B29C 67/00 - Shaping techniques not covered by groups , or
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
G05B 19/4097 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by using design data to control NC machines, e.g. CAD/CAM
88.
MATRIX FOR AN AIR/OIL HEAT EXCHANGER OF A JET ENGINE
The invention relates to a matrix (30) for a heat exchanger between a first fluid and a second fluid, in particular for an air/oil application in a turbomachine. The matrix (30) comprises: a cross-passage in which the first fluid can flow; a grid with tubes (34) extending in the cross-passage and in which the second fluid circulates. The grid supports at least two fins (38; 40) that are in succession in the flow of the first fluid, in particular cooling fins. These successive fins (38; 40) extend in the first fluid along principal directions that are inclined with respect to one another.
F28F 1/38 - 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 being staggered to form tortuous fluid passages
F28D 7/16 - 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 in parallel spaced relation
F28F 1/12 - 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
F28F 1/34 - 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 obliquely
A fluid valve includes a valve member located between a first cavity and a second cavity, and an actuator that includes a pilot. The valve member is moved by the balance between the pressure prevailing in the first cavity and the pressure prevailing in the second cavity. The valve member includes a longitudinal hole that can be blocked by the pilot so as to modify the pressure prevailing in the first cavity and the force acting on the valve member so as to vary a fluid flow rate between an inlet and two outlets. The valve member is attached to a piston, one end of which is located in a third cavity. The force acting on the valve member is determined by the pressures prevailing in the various cavities.
F16K 31/40 - Operating meansReleasing devices actuated by fluid in which fluid from the conduit is constantly supplied to the fluid motor with electrically-actuated member in the discharge of the motor
F16K 31/42 - Operating meansReleasing devices actuated by fluid by means of electrically-actuated members in the supply or discharge conduits of the fluid motor
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
The invention concerns a support casing (24) for a rotor (12) of a turbine engine such as a ducted fan turbojet engine used for propulsion of an aircraft. The casing (24) comprises: an outer annular wall (38) with an inner annular surface (44); an inner hub (40) able to support the rotor (12) of the axial turbine engine and comprising an outer annular surface (42); an annular passage (46) between the annular wall (38) and the inner hub (40); an annular row of arms (48) passing radially through the annular passage (46). Each arm (48) of the casing (24) comprises an orifice (50) arranged in the annular passage (46) radially at the level of one of said annular surfaces (42; 44). Inserts are fitted to the orifices (50) to control the flow passing through.
F01D 9/06 - Fluid supply conduits to nozzles or the like
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
F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
A test bench for turbomachine comprising: an installation zone for turbomachine; an active system for attenuating the noise emissions produced by the turbomachine. The active system includes an attenuation zone with emitters such as loudspeakers; a first microphone placed downstream of the turbomachine; and a second microphone placed downstream of the attenuation zone. The system reduces the turbomachine waves on the basis of the measurements from the first microphone and from the second microphone. The invention also proposes a method for attenuating the noise emissions from the turbomachine tested in the test bench.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
G01M 15/12 - Testing internal-combustion engines by monitoring vibrations
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
G10K 11/178 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using interference effectsMasking sound by electro-acoustically regenerating the original acoustic waves in anti-phase
92.
Inner shroud and orientable vane of an axial turbomachine compressor
An assembly for the compressor stator of a turbomachine. The assembly comprises: a shroud, in various instances an inner shroud, that is axially divided into two parts; a pocket formed in the shroud; a bearing located in the pocket; and an orientable vane pivotably mounted in the bearing about a pivot axis. The shroud comprises an axial interface separating the parts that is axially offset from the pivot axis of the orientable vane. The invention also provides a process for assembling the assembly.
The invention concerns an assembly for the stator of a compressor of an axial-flow turbine engine, such as a low-pressure compressor of the turbojet engine also known as a booster. The assembly comprises: a first annular array of first vanes of the stator extending radially in the axial flow; and a second annular row of second vanes of the stator, with controlled orientation, also known as variable-pitch vanes or VSV. In addition, the assembly comprises an external monobloc shroud on which the first vanes and the second vanes are mounted in a pivoting manner.
An oil tank fitted to a turbomachine, for example an aeroplane turbo-jet engine. The tank includes an inner chamber containing the oil of the turbomachine, a wall with an inner surface surrounding the inner chamber, and a capacitive device for measuring the oil level. The device includes at least one electrode and potentially two parallel electrodes forming the inner surface. These electrodes are immersed in the oil to measure the oil level by measuring capacitance. A method for manufacturing a tank in which the electrodes are printed on the wall.
G01F 23/26 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
A system for controlling a variable orientation vane of a turbomachine compressor, for example a low-pressure compressor of a turbojet engine. Such a vane is also known as a variable stator vane. The system comprises a support, an orientable vane that is movable in rotation relative to the support and that comprises a lever for controlling the orientation of the orientable vane (26), and a magnetic field source that defines an air gap with the lever. When the source is powered electrically, it forms an electromagnet attracting the lever by induction such that the orientable vane changes orientation.
An internal gear pump includes a pinion, a ring arranged around the pinion, and a cylindrical wall arranged around the ring. A support element, on which the pinion and the ring are supported, carries high-pressure liquid towards a recess located at the junction between the ring and the cylindrical wall, and also carries low-pressure liquid towards another recess located at another point of the junction between the ring and the cylindrical wall. The recess allows the load of the ring on the cylindrical wall to be reduced.
F04C 2/10 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of internal-axis type with the outer member having more teeth or tooth-equivalents, e.g. rollers, than the inner member
F01D 15/08 - Adaptations for driving, or combinations with, pumps
F04C 2/08 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
F04C 15/00 - Component parts, details or accessories of machines, pumps or pumping installations, not provided for in groups
F04C 15/06 - Arrangements for admission or discharge of the working fluid, e.g. constructional features of the inlet or outlet
B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
97.
Augmented-reality test method and test bench for a turbine engine
A method for testing a turbojet engine for an aircraft in a U-shaped or open-air test bench includes: (a) visual inspection of the test bench and of the turbojet engine; and (b) testing of the turbojet engine in the test bench. During the test, the turbojet engine bears test equipment with sensors, other sensors being housed in the test bench. The test bench includes an augmented-reality system performing the step of (a) visual inspection in the test bench in order to detect a possible major anomaly in the test bench. The step of (a) visual inspection is intended to check the conformity of the test conditions, and especially those of the test equipment or that of the test bench as a whole. The method performs the step of (b) testing only in the absence of an anomaly.
The present invention relates to a handling system comprising a rolling bridge (3) with a lifting system (32). The lifting system (32) can be moved in a first direction (11), a second direction (12) and potentially in a third direction (23) and potentially in a fourth direction (24) by an operator by means of a control device (4) close to the rolling bridge (3). Each direction of movement (11, 12, 23, 24) corresponds to a symbol (61-64) on the control device (4), and this symbol (61-64) is reproduced on visual communication means (51-54) on walls of the handling system premises.
B66C 13/16 - Applications of indicating, registering, or weighing devices
B66C 17/00 - Overhead travelling cranes comprising one or more substantially-horizontal girders the ends of which are directly supported by wheels or rollers running on tracks carried by spaced supports
99.
SENSOR FOR DETECTING PARTICLES IN A FLUID OF A LUBRICATION SYSTEM
The present invention relates to a particle sensor (1) provided for detecting particles in a duct (4) of a lubrication system. The sensor (1) comprises a measurement unit (2), arranged so as to be placed in contact with a fluid flowing through the duct (4), and a reference unit (3), arranged so as to be placed out of contact with the fluid flowing through the duct (4). Particles are detected by comparing electrical signals arising from the measurement unit (2) and from the reference unit (3).
G01V 3/10 - Electric or magnetic prospecting or detectingMeasuring magnetic field characteristics of the earth, e.g. declination or deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices using induction coils
F16H 57/04 - Features relating to lubrication or cooling
G01N 15/06 - Investigating concentration of particle suspensions
A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.
A62C 99/00 - Subject matter not provided for in other groups of this subclass
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
patents
