Abstract: The invention relates to a heat exchanger that is configured to permit an exchange of heat between a first fluid and a second fluid that circulate in passage paths formed by plates (14a, 14b) and fins (16a, 16b) of the heat exchanger, the fluids flowing in a multitude of passage channels (10) each consisting of a closed space (12) delimited by two adjacent plates and two adjacent fins, characterized in that each plate extends along a non-planar surface following at least a first oscillating curve, and each fin further following at least one second oscillating curve along at least one second main direction, in such a way that each passage path allows the fluid to flow in the closed space along a fluid direction defined by a generatrix that is a combination at least of the first oscillating curve and the second oscillating curve.

Abstract: A method for manufacturing an electrically conductive composite material includes obtaining a composite material which includes a thermoplastic matrix and short carbon fibers and is free of carbon nanotubes, preheating a furnace until a predetermined target temperature is reached, inserting the composite material into the preheated furnace once the target temperature has been reached, and heating the composite material in the furnace at the predetermined target temperature which is kept constant for a predetermined duration.

Abstract: The invention relates to an air conditioning system for a cabin (10) of an aircraft (80) comprising: a bleed air source (12); a ram-air circulation channel (13); a network of pipes and control valves; an air cycle turbine engine comprising at least one compressor (3) and a power turbine (4) which are mechanically connected to one another; and at least one primary cooling exchanger (PHX) which is accommodated in said channel (13), characterized in that said pipe network comprises a thermal power pipe (53) which is suitable for being able to fluidically connect, upon control of at least one control valve (25, 21), said air outlet (4b) of said power turbine (4) and said ram-air circulation channel (13) upstream of said primary exchanger (PHX) so that said bleed air expanded by said power turbine (4) can form a thermal energy source for said ram air being supplied to said primary circuit of said primary exchanger (PHX).

Abstract: The invention relates to an air conditioning system for an aircraft comprising a turbine engine comprising at least one radial turbine and a compressor, said radial turbine extending along a central axis (10) and comprising a wheel (20) equipped with vanes (21) mounted so as to be able to rotate about said central axis (10), a nozzle (30) arranged at the periphery of said wheel (20) comprising a plurality of variable-pitch blades (31) arranged around said central axis (10), and a volute (12) comprising an air inlet (12a) and an air outlet (12b) opening onto said plurality of variable-pitch blades (31), characterized in that said variable-pitch blades (31) are arranged around said central axis (10) between two nozzle casing walls (11a, 11b) delimiting an air passage section of said nozzle between them, each variable-pitch blade (31) further comprising means for axial displacement of the blade between the two casing walls (11a, 11b).

Abstract: The invention relates to a device forming a foil air bearing, comprising a cylindrical sleeve (10) extending along a longitudinal direction, and having an inner surface (11) which defines a central bore, characterized in that it further comprises: at least one longitudinal notch (40, 50, 60) formed in said cylindrical sleeve and opening radially into said central bore; a first peripheral inner lining, called the bump lining, comprising at least one metal foil equipped with radial projections, called the bump foil (22, 23, 24), each bump foil having, at each end, a radial tongue, called the radial bump tongue (22a, 22b, 23a, 23b, 24a, 24b), housed freely in a longitudinal notch (40, 50, 60); a second peripheral inner lining, called the top lining, comprising at least one metal foil, called the top foil (32, 33, 34), each top foil having, at each end, a radial tongue, called the radial top tongue (32a, 32b, 33a, 33b, 34a, 34b), housed freely in a longitudinal notch (40, 50, 60).

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 of an air-conditioning system of a cabin of a transport vehicle, comprising: a primary circuit supplied by a first air flow (169), a secondary circuit supplied by a second air flow (168), a casing (161) defining an air-circulation enclosure (162), a primary circuit inlet box (164) allowing entry into said air-circulation enclosure, and a primary circuit outlet box (165) allowing exit from the air-circulation enclosure, characterized in that said inlet box (164) is mounted removably on said casing (161), and in that it houses a three-dimensional structure (163) forming a catalytic and/or adsorbent support for treating the air of said primary circuit, and a means for distributing said first air flow into said heat-exchange matrix.

Abstract: Air conditioning system for a cabin of an air or rail transport vehicle, comprising: a pneumatic turbine engine that comprises at least one compressor and at least one turbine (126) and is connected by a mechanical shaft extending along an axis, referred to as the turbine engine axis (132), said turbine comprising an air inlet and an air outlet; and a water extraction loop that comprises a heater (110), a condenser (112) and a water separator (114), is fluidically arranged between an air outlet of the compressor and the air inlet of said turbine (126), and is configured to dry the air supplied to said turbine (126), characterized in that said heater (110), said condenser (112), and said water separator (114) are arranged in series on the turbine engine axis (132) or around said axis, forming the air inlet of said turbine (126).

Abstract: The invention relates to an air bleed system comprising an air bleed port provided on an engine of an aircraft, an air supply pipe, a pressure sensor, a pressure relief valve mounted in said air supply pipe, characterized in that said pressure relief valve comprises: a valve body (11); a closure member (121) pivotally mounted in said air circulation duct; and an air discharge channel (13) passing through said valve body (11); at least one air discharge opening (15) formed on said upstream face of said closure member (121) and at least one air evacuation opening (19) which opens out to the outside of the air circulation duct.

Abstract: A valve for controlling a fluid flow includes a valve body, a shutter component configured to be able to transition from an open position allowing the circulation of fluid, to a closed position preventing the circulation of fluid. The component is characterized in that it includes a fixed conical support integral with the valve body, a conjugate conical flap rotationally movable relative to the fixed support, and fluid passage apertures respectively arranged in the conical flap and in the fixed support, and an actuator of the shutter component adapted to be able to control the position of the shutter component.

Abstract: A fluid flow control valve includes a valve body, a closing member arranged in the valve body and configured so that it can have at least one first position, called the open position, in which it allows the flow of fluid to flow freely in the valve body, and at least one second position, called the closed position, in which it prevents the fluid flow from flowing in the valve body between the fluid inlet and the fluid outlet, an electric actuator of the closing member that is suitable for being able to control the position of the closing member in the valve body, characterized in that the electric actuator is arranged in the valve body so that it can be cooled by the flow of fluid flowing in the valve body.

Abstract: The invention relates to a method for supplying air at a controlled temperature to a cabin of a surface vehicle in which at least one air cycle device is used, comprising at least one motorized turbocompressor. The air inlet of the turbine is arranged to receive a compressed airflow from the compressor. At least one exchanger is interposed between the air outlet of the compressor and the air inlet of the turbine. The air inlet of the compressor is arranged to receive air at a pressure greater than or equal to atmospheric pressure. The invention likewise relates to a surface vehicle comprising at least one such air cycle device.

Abstract: The invention relates to a system for environmental control of an aircraft cabin (5), comprising a device for bleeding compressed air from at least one aircraft engine; an air cycle turbine engine (20) comprising at least one supercharger (21) connected to said device for bleeding compressed air by an air bleed duct (7) and a turbine (22) connected to the cabin (5) by a cabin inlet duct (8) in order to be able to supply said cabin with air at a controlled pressure and temperature, characterised in that it further comprises: stationary blading (23) which has a variable injection cross section and is mounted on said turbine (22) of said air cycle turbine engine (20) so as to be able to modify, on command, the flow rate and/or the pressure of air supplying an air inlet of said turbine (22); and a second supercharger (22) which is mounted on said air cycle turbine engine (20) and is connected to a device for bleeding outside air and to said bleed duct.

Abstract: The invention relates to a torque motor comprising a stator and a rotor that extend along a common central axis. The stator includes an integral magnetic body and at least one pair of radial teeth that extend along the central axis and define slots for receiving stator windings, and at least one permanent magnet supported by the integral magnetic body. The torque motor also includes a winding support for the stator windings that has a hollow body that extends along the central axis and that delimits a chamber for receiving the rotor, and cavities for receiving the stator windings. In this way, the stator windings are integrated in the stator by the winding support, fitted with the stator windings, being axially inserted into the integral magnetic body.

Abstract: Disclosed is a method and a device for thermally controlling a plurality of cabins of a vehicle from a mixing chamber supplied with air from at least one air supply device of which at least the temperature is controlled, each cabin being supplied with air by a supply conduit specific to this cabin. At least one cabin is supplied with air at a temperature adjusted by at least one individual exchanger associated with the supply conduit specific to this cabin, in which a second circuit is supplied with a heat transfer fluid from at least one heat transfer fluid thermal regulation loop of the vehicle. Also disclosed is a vehicle provided with at least one thermal control device.

Abstract: A method for coating a turbomachine part with a self-lubricating includes: providing a rotor or thrust disc of the turbomachine; applying, by a thermal spraying process, a self-lubricating coating having of a mixture of 50 to 90 wt % of alumina (Al2O3) with titanium oxide (TiO2) to a surface of the rotor and/or a surface; and finishing the coated surface of the rotor and/or thrust disc.

Abstract: A compression device includes at least: two interleaved scrolls each of which is made of an aluminum alloy, one of the scrolls, being a fixed scroll (3), and is fixed and the other scroll, which is an orbiting scroll and moves eccentrically without rotating. Also included are anti-rotation means made of an aluminum alloy and configured to allow anti-rotation of the orbiting scroll. The compression device also includes one flat thrust bearing configured to axially contain the orbiting scroll and is made of aluminum alloys or grades of cast iron. The compression device also includes coatings for promoting friction between the fixed scroll, the orbiting scroll, the anti-rotation means and the flat thrust bearing.

Abstract: A rotor assembly is presented for a turbine engine with gas bearings including a solid permanent magnet with no central bore. The rotor assembly also includes a first shaft having at least one bearing intended for engaging with a support bearing to form a gas bearing and ensure rotational guidance of the first shaft as well as a thrust disk. The solid permanent magnet is press-fitted inside a band made of a nonmagnetic material, the band is integral with the first shaft in an extension thereof, and a second shaft has at least one bearing intended for engaging with a support bearing to form a second gas bearing and ensure rotational guidance of the second shaft, coaxially with the first shaft such that the first shaft, the band, and the second shaft form an integral assembly.

Abstract: Disclosed is a method for ventilating a ram air channel for a vehicle—in particular an aircraft—including at least one heat exchanger. The ram air channel is provided with a jet pump including a plurality of compressed air inlets connected to a plurality of separate compressed air sources of the vehicle, and a plurality of compressed air outlet nozzles. At least two nozzles are independently connected to at least two separate compressed air sources of the vehicle.

Abstract: A method for coating a turbomachine part with a self-lubricating includes: providing a rotor or thrust disc of the turbomachine; applying, by a thermal spraying process, a self-lubricating coating having of a mixture of 50 to 90 wt % of alumina (Al2O3) with titanium oxide (TiO2) to a surface of the rotor and/or a surface; and finishing the coated surface of the rotor and/or thrust disc.