Abstract: Cryogenic turbopump feed line, comprising a main channel able to transport a cryogenic fluid, a plurality of secondary channels parallel to and disposed around the main channel in which the plurality of secondary channels are disposed on the periphery of an external perimeter of the main channel.

Abstract: The invention relates to a device (200) for liquefying a gas (51), the device comprising: a circuit (55) for conveying gas to be liquefied, the circuit comprising at least one heat exchanger (204) for exchanging heat between the gas (51) to be liquefied and a refrigerant flow (52) comprising at least dihydrogen refrigerant; a closed refrigeration circuit (210) configured to convey the refrigerant flow, the closed refrigeration circuit comprising a means (215) for maintaining an internal composition of the dihydrogen refrigerant at a ratio of parahydrogen to orthohydrogen that is lower or higher than the ratio corresponding to a natural equilibrium composition in the refrigerant flow closed circuit, the means (215) comprising a catalytic reactor (220) configured to convert some of the orthohydrogen from the dihydrogen refrigerant flow into parahydrogen or vice versa.

Abstract: A system for recovering compression energy from a gas, the system comprising an organic Rankine cycle module and an adiabatic compressor, the organic Rankine cycle module comprising a heat transfer fluid and the adiabatic compressor comprising N adiabatic compression stages for the gas, N being greater than or equal to 2, and, downstream of each adiabatic compression stage, two heat exchangers, a first heat exchanger configured to extract heat from the gas leaving the adiabatic compression stage and to heat the heat transfer fluid passing through the first heat exchanger and a second heat exchanger configured to extract heat from the gas leaving the first heat exchanger to a cold source passing through the second heat exchanger. A liquefier comprising such a system and method for recovering compression energy from a gas.

Abstract: Method for hydrogen liquefaction comprising at least one precooling step, wherein a hydrogen feed flow is cooled by a first refrigerant, a cooling step, wherein the hydrogen feed flow is cooled by a second refrigerant, and a step of expanding the hydrogen feed flow. Each of the first and second refrigerants is successively subjected to at least one compression and to at least one expansion in order to cool it, and a liquid phase of the first refrigerant cools the second refrigerant between at least three stages of said compression so that the second refrigerant does not exceed a temperature of 150 K, optionally 113 K, during said compression of the second refrigerant.

Abstract: A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.

Abstract: A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.

Abstract: Cryogenic turbopump feed line, comprising a main channel able to transport a cryogenic fluid, a plurality of secondary channels parallel to and disposed around the main channel in which the plurality of secondary channels are disposed on the periphery of an external perimeter of the main channel.

Abstract: The invention relates to the field of cryogenics, and in particular to a device and a method for chilling down a cryogenic system (1). The chilldown device (100, 101) comprises a cryogenic fluid feed circuit (102, 103) and at least one atomizing nozzle (110) connected to said feed circuit (102, 103). The chilldown method includes feeding cryogenic fluid via a feed circuit (102, 103) to at least one atomizing nozzle (110) connected to the feed circuit (102, 103), spraying the cryogenic fluid through the at least one atomizing nozzle (110) as a spray (200) of cryogenic fluid, and projecting the spray (200) of cryogenic fluid against at least one zone to be cooled in the cryogenic system (1).

Abstract: A casing (20) of a propellant feed turbopump (10) for a rocket engine (50), the casing including a cooling circuit (30), wherein the cooling circuit is formed at least in part in a wall of said casing (20).

Abstract: A system (100) for feeding propellant to an igniter, the system comprising: a tank (10) presenting an admission (11) and an outlet (12); a liquid propellant feed line connected to the admission (11) of the tank (10); and a propellant outlet line connecting an outlet (12) of the tank (10) to an igniter (40); the system being characterized in that said tank (10) presents an inside volume filled with heat storage spheres (20), said storage spheres (20) being adapted to store heat and to transmit it to a fluid passing through said tank (10), in such a manner as to vaporize a liquid propellant passing through said tank (10).