Abstract: The invention relates to a supply device for compressed air to a plurality of cathodes (100a-100d) of a fuel cell system, characterized in that it comprises a motorized compressor (12) configured to provide a source of compressed air to all of the cathodes (100a-100d), a group of ducts configured to conduct the compressed air to each cathode (100a-100d), for each cathode (100a-100d), a proportioning valve (20a-20d) upstream or downstream of said cathode (100a-100d) which is configured to regulate the flow rate of compressed air passing through said cathode (100a-100d), anti-pumping protection means (30, 32) configured to allow the flow of a minimum flow rate of compressed air leaving the compressor (12), and a control device (24) configured to control the speed of the compressor (12) and the opening or closing of each proportioning valve (20a-20d) and/or the operation of the anti-pumping protection means (30, 32).

Abstract: Exchanger (16) for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels (80) for the circulation of the secondary air; and a plurality of channels for the circulation of the primary air, characterized in that said exchanger further comprises: water circulation channels (83) each extending adjacently to a secondary channel (80); water-spray micro-perforated hollow bars (63) each extending adjacently to a primary channel (60) and fluidically connected to the micro-perforated hollow bars in order to be able to heat the water by interaction with the primary air before said water is sprayed into the flow of primary air at the inlet of the exchanger.

Abstract: The invention relates to a device (30) for cooling heat-sensitive control members (29) of a pneumatic or electropneumatic valve (20), comprising a containment casing (31) designed to contain said control members (29): a fresh air inlet (32) in said containment casing (31); an air outlet (33) of said containment casing, provided with a ventilation air tube (34) that comprises: an air acceleration column (35) which puts into fluidic communication said containment casing (31) and the air outlet (33); a primary supply (37) for supplying the acceleration column (35) with primary air; a secondary supply (38) for supplying the acceleration column (35) with secondary air, provided in said containment casing (31) such that the primary air can drive and accelerate the secondary air in the direction of the air outlet so as to produce forced air ventilation in said containment casing (31) between the air inlet (32) and the air outlet (33).

Abstract: Air conditioning system for an aircraft cabin, comprising a primary exchanger (14) configured to cool bleed air (12) from at least one compressor of the aircraft, a pre-compressor (18), an intermediate exchanger (20), a main compressor (22) configured to compress said pre-compressed bleed air, a main exchanger (28) configured to cool the compressed bleed air, and a water extraction loop, characterized in that it comprises a duct (108) for recovering at least part of the air from the cabin after it has passed through the cabin, and recovered air circulation ducts configured so that the recovered air successively passes through: a secondary exchanger (34), the recovered air forming a first cold source for cooling the bleed air again, a heat exchanger (20), the recovered air forming a second cold source for cooling the bleed air, an energy recovery turbine (48), the recovered air forming a source of energy.

Abstract: Heat exchanger with plates, which is configured for a heat exchange between a hot fluid and a cold fluid, comprising at least one core band (130a, 130b) arranged in order to maintain the sealing tightness, a plurality of closing bars (138) defining, with the closing plates, flow channels, characterized in that the core band (130a) arranged at a cold pass inlet and at a hot pass inlet comprises an inlet (132) for supplying hot air, and in that at least one closing bar (138) arranged in the lengthwise direction of the inlet of the cold pass comprises an inlet for said hot air and a flow circuit for said hot air in a U shape and comprising two sections, each extending over the whole length of the closing bar, a hot air outlet for expelling the hot air in the hot pass, and an intermediate section forming the base of the U.

Abstract: Described herein is the location of an air leak in a network for supplying pressurized air that includes one or more components and at least one leak detection loop including one or more sensing elements. The location includes receiving information representative of detection of the leak by a sensing element of the detection loop, receiving a 3D model of at least part of the network for supplying pressurized air, interrogating a database associating a leak site of a component with each location on the detection loop, determining a precise location of the leak on the network for supplying pressurized air, mapping the precise location relative to a component, and instructing display of the 3D model corresponding to the component of the supply network and of the precise location.

Abstract: A heat exchanger includes a fluid flow tube configured to allow an exchange of heat between the fluid flowing in the tube and an enclosure surrounding the tube. The enclosure is formed from two profiled bars configured to surround the tube over at least one part of its length. Each of the bars includes a recess adapted to receive the tube, and a joint surface configured to form a joint with the other profiled bar. The joint surfaces of the profiled bars form a gap therebetween. As well, the joint surfaces of the profiled bars are arranged in different planes such that the gap forms at least one baffle on each side of the tube.

Abstract: The invention relates to a system for cooling a fuel cell assembly (10) of a transport vehicle, such as an aircraft, comprising: a cooling fluid circulation loop (20); a cooling heat exchanger (24) configured to be able to provide heat exchanges between said loop (20) and a channel (25) for circulating cooling air (26); a variable-speed pump (21) for supplying said cooling loop with cooling fluid as a function of a measurement representative of the cooling need of said fuel cell assembly; for each fuel cell (10a, 10b, 10c) of said cell assembly, a 3-way valve (12a, 12b, 12c) for regulating the flow rate of cooling fluid supplying this cell as a function of a measurement representative of the cooling need of this cell.

Abstract: The invention relates to an air-conditioning system for an aircraft cabin (5) comprising: an engine air bleed device (10); an air-conditioning pack (20) comprising a pack air inlet (21) connected to said engine bleed device (10), and a pack air outlet (22) connected to said cabin (5); an auxiliary module (50) for supplying pressurized air comprising an auxiliary turbomachine (51), comprising a compressor (52) supplied with external fresh air and a turbine suitable to be able to be supplied with air coming from the engine bleed device; and a control unit configured to activate either a standard mode in which the pack air inlet is supplied with the pressurized air coming from the engine bleed device (10), or a fresh air mode in which said pack air inlet (21) is supplied with the pressurized air coming from the auxiliary module (50).

Abstract: System for protecting an outer surface of an aircraft comprising at least two fuel cells (112, 212) from icing, characterized in that it comprises a first and a third liquid circuit (114, 214) each causing a cooling liquid of the fuel cells (112, 212) to flow, a second and a fourth liquid circuit (118a, 118b) each causing an icing protection liquid to flow, at least two icing protection heat exchangers (120a-d, 220a-d) arranged on the outer surface of the aircraft and having each icing protection liquid pass through them when it flows in the second or fourth liquid circuit (118a, 118b), and two liquid-liquid heat exchangers (116, 216) in which the cooling liquids form a hot pass and the icing protection liquids form a cold pass to reheat the icing protection liquid by the heat from the cooling liquids.

Abstract: The invention relates to a profiled part (12) for a heat exchanger, configured to have at least one fluid flow tube (14) passing through it, comprising, for each flow tube (14), a hollow cylinder (18) comprising an inner surface configured to receive said flow tube (14), the cylinder (18) having an inner diameter which is substantially equal to the outer diameter of said flow tube (14). The profiled part (12) is characterized in that the profiled part comprises a slit (16) extending over the whole length of the cylinder (18) and configured to permit, by application of at least one mechanical force to the profiled part, a modification in the inner diameter of the cylinder (18) in order respectively to permit the insertion of the tube into the cylinder (18) or the clamping of the tube (14) by the inner surface of the cylinder (18). The invention also relates to a heat exchanger (10) comprising such a profiled part (12) and a flow tube (14).

Abstract: The invention relates to a regulator, configured to receive a hot air flow via an air inlet (12), to treat this hot air and to transmit the treated hot air to an air outlet (14) configured to supply a pneumatic actuator (16), comprising at least one temperature-sensitive electrical and/or mechanical element (36, 37), and a regulator body (100). The regulator is characterized in that the regulator body is composed of a heat-conducting hollow enclosure (28) at least partially surrounding a duct (22) for transporting the hot air flow, said cavity being at least partially filled with a metal mesh produced by additive manufacturing that allows the cooling air to circulate, and in that the temperature-sensitive electrical and/or mechanical element (36, 37) is arranged in, or in contact with, the regulator so as to be cooled by the cooling air by thermal conduction.

Abstract: Vibration absorbing device comprising a housing (12), a membrane (14) enclosed in the housing (12) and thus forming two chambers (18a, 18b) in the housing (12), said chambers (18a, 18b) being filled with a fluid, at least one weight (16), arranged on the membrane (14) in order that a movement of the weight (16) causes a movement of the membrane (14), and at least one duct (24) arranged to permit the fluid to flow between the two chambers (18a, 18b) if the membrane (14) and the weight (16) move.

Abstract: A heat-exchange device includes a flow enclosure defined by two external plates, a first inlet and a first outlet for a first heat-transfer fluid, a second inlet and a second outlet for a second heat-transfer fluid, and an exchanger block with plates disposed in the flow enclosure so as to be in fluid communication with the inlets and outlets in order to permit the flow of the first fluid and of the second fluid into and through this exchanger block and the transfer of calories therebetween. Each external plate has at least one hollow. An air-conditioning system may include such device and an aircraft, in turn, can include such air-conditioning system.

Abstract: A tubular heat exchanger (10) comprising: a fluid circulation chamber (20) intended to be supplied with a first fluid, referred to as outer fluid, brought to a first temperature, a heat exchange matrix (30) housed in said circulation chamber and formed by a plurality of heat exchange tubes (31) each comprising at least one pair of ducts (32; 33) nested one inside the other, extending along a direction, referred to as longitudinal direction, and defining: a channel for circulating a fluid, referred to as inner channel (32c; 33c), suitable for being able to be supplied with a second fluid, referred to as inner fluid, brought to a second temperature, and a channel for the circulation of a fluid, referred to as intermediate channel (32d; 33d), and suitable for being able to be supplied with a third fluid, referred to as intermediate fluid, brought to a third temperature, different from said first temperature.

Abstract: Disclosed is a device for supplying pressurised air to a cathode (110) of a fuel cell (100), comprising a compressor (12) connected to an air inlet pipe (14) and to an inlet (112) of the cathode, configured to receive air originating from the air inlet pipe (14), compress it and supply it to the cathode (110), a motor (16) configured to drive the compressor (12) and surrounded by a casing (18), a recovery turbine (26) configured to expand the water-laden air (24) originating from the outlet (114) of the cathode in order to supply this expanded air (28) via an outlet of the turbine (26). The device is characterised in that it comprises a cooling channel (32) configured to receive at least some of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).

Abstract: The invention relates to a driven turbocompressor of an air conditioning system, comprising a compressor (12) which is connected to an air intake duct (14) and to an inlet (112) of a cabin of a vehicle, and is configured to receive air from the air intake duct (14), to compress it and to provide it to the cabin, a motor (16) that is configured to drive the compressor (12) and is surrounded by a casing (18), a recovery turbine (26) that is configured to expand the cabin air (24) coming from an outlet (114) of the cabin. The device is characterized in that it comprises a cooling duct (32) configured to receive at least part of the expanded air (28) so as to cool the casing (18) of the motor and the motor (16).

Abstract: The invention relates to a system for cooling a fuel cell (10) of a transport vehicle such as an aircraft, comprising: a cooling heat exchanger (30) configured to be able to exchange heat between a loop (20) for cooling the cell and a channel for circulating dynamic air; a device (22, 23) for recovering water produced by said fuel cell; a tank (25) for storing recovered water; a device (50) for spraying water into said dynamic air channel (40) upstream of said heat exchanger (30); and a computer (28) for controlling the amount of sprayed water on the basis of a measurement representing the temperature of said fuel cell (10).

Abstract: The invention relates to a distributor for a turbomachine radial turbine, comprising an annular grill (26) extending about a central axis (10) and comprising a plurality of variable-pitch blades (31), defining between them an air passage cross section, characterized in that each blade is rotatably mounted about a pivot shaft (32), itself moveable in a translation direction, comprising at least one radial component, such that said blade may, upon actuation of control means (40), be pivoted about the pivot shaft and/or moved in relation to the central axis in said translation direction so as to be able to modify the air passage cross section by respectively controlling the metal angle (?3) and the radial spacing (?R).

Abstract: The invention relates to a module (23) for recovery of energy of an aircraft cabin (5) comprising at least one air outlet (16) from the cabin and at least one fresh air inlet (15) into the cabin, the said module comprising: a turbine engine (30) comprising a compressor (31) and a turbine (32) mechanically coupled to one another; a cabin-air recovery duct (42) designed to be able to link the air outlet (16) from the cabin and the said turbine (32); a cabin-air injection duct (41) designed to be able to link the compressor (31) and fresh air inlet (15) into the cabin; an emergency duct (43) designed to be able to link a high-pressure air source and the said turbine (32); a control unit (25) configured to be able, according to predetermined operational conditions, to activate either a routine mode, in which the said turbine (32) is exclusively supplied by the air evacuated from the cabin (5), or an emergency mode, in which the said turbine (32) is exclusively supplied by the air provided by the high-pressure air