Abstract: A method of fabricating a ceramic turbine blade, the method includes selective melting on a powder bed in order to obtain a blade mold cavity in a mold, a ceramic-based suspension is provided, the suspension is introduced into the blade mold cavity, the suspension is subjected to a gelation step in the mold cavity in order to obtain a blade suitable for being extracted from the mold cavity, and the blade is extracted from the mold cavity.

Abstract: An assembly including a fuel cell arranged in a housing, the fuel cell includes an anode having an admission and an anode discharge, and a cathode having an oxygen admission and a cathode discharge, the assembly includes the housing and a sealed enclosure in which the fuel cell is arranged and configured in such a manner that the gas discharged by the fuel cell is discharged into the sealed enclosure so as to generate an over-pressure of oxygen-depleted air inside the sealed enclosure.

Abstract: The invention relates to a device for starting a gas turbine, comprising an initiation system able, on command, to rotate said gas turbine. The starting device comprises means for receiving information representing the rotation speed of the gas turbine, means for calculating a set torque value according to said information representing the rotation speed of the gas turbine, and means for transmitting said set torque value to the initiation system, and the means for calculating the set torque value are suitable for making a comparison of the information representing the rotation speed of the gas turbine with a predetermined speed profile and calculating the set torque value from said comparison.

Abstract: The invention relates to a device (30, 31, 39, 42) for preheating a fluid for supplying fuel injectors, comprising a fuel circuit comprising an electric pump (12, 44) controlled by an electronic power module (18). A bypass pipe (27) makes it possible to allow or prevent the flow of fuel to the equipment. According to the invention, the device comprises means for increasing the pressure difference between the inlet and outlet of the pump (22, 44), these means being arranged in the bypass pipe (27).

Abstract: An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.

Abstract: A kit for forming a bipolar plate of a fuel cell, the kit comprising two half-plates (1A, 1B) adapted to be assembled one against the other, each of the two half-plates (1A, 1B) having grooves (11A, 12A, 11B, 12B) formed by embossing and extending in a longitudinal direction (X-X), and being adapted to form reagent flow channels (5A, 5B) on either side of the half-plates (1A, 1B), together with heat transfer fluid flow ducts (6) between the two half-plates (1A, 1B), the kit being characterized in that the half-plates (1A, 1B) are identical, each having at least one pair of complementary indexing elements (2A1, 2A2, 2B1, 2B2, 3A1, 3A2, 3B1, 3B2) made by embossing and adapted to center said half-plates (1A, 1B) relative to each other when they are assembled together.

Abstract: The invention relates to a starting device for an auxiliary power unit (10), comprising a control unit (32) of the power supply of a starter motor (12), said motor (12) being suitable to be supplied with power by a supply network (16) and configured to drive a revolution of the auxiliary power unit (10), the control unit (32) being suitable to receive an item of information representative of the speed of rotation of the auxiliary power unit (10) and control of the power supply of the starter motor (12) by the control unit (32) being dependent on said item of information representative of the speed of rotation. The device is characterised in that the control unit (32) is suitable to receive an item of information representative of the voltage of the power supply network (16) and in that control of the power supply of the starter motor (12) by the control unit (32) is dependent on said item of information representative of the voltage.

Abstract: An aircraft turboprop engine includes at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the supply means has at least one compressor borne by the gearbox and of which the rotor is coupled to the low-pressure body by means of the gearbox.

Abstract: An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a first gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein said supply means has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.

Abstract: The invention relates to an aircraft turboprop engine (310) comprising at least a low-pressure body (12) and a high-pressure body (14), possibly also an intermediate-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propeller by means of a first gearbox (16), the turboprop engine also comprising means for supplying air to an air-conditioning circuit of an aircraft cabin, characterised in that said supply means comprise at least one compressor (60) of which the rotor (61) is coupled to the low-pressure body, said load compressor (60) including an air inlet (62) connected to means (72) for bleeding air from the compressor of the turboprop engine when all of the aforementioned bodies comprise only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies comprise at least two compressors.