A propulsion system 100 comprises a propulsive hydrogen-burning gas turbine engine 190A, a first tank 106 storing liquid hydrogen with an ullage 105 and a first fuel line 108 including a fuel pump 112 and a vaporiser 116, the first fuel line providing gase...

An aircraft propulsion systems (400) has an aircraft systems (404) including at least one hydrogen tank (432) and an aircraft-systems heat exchanger (458) and engine systems (402) includes at least a main engine core, a high pressure pump (416), a hydrogen...

An aircraft propulsion system fuel system (224) comprises a fuel line (217) configured to receive liquid hydrogen fuel from a fuel tank (104), a vaporizer (612) configured to vaporize liquid hydrogen fuel from the fuel line to generate a supercritical or g...

The invention relates to an aircraft comprising at least one propulsion system, at least one debris ejection zone (ZE) (52) originating from the propulsion system, and at least one fluid supply circuit (26). The latter comprises a shutter (34) configured t...

L'invention a pour objet une enceinte (14) contenant un gaz d'inertage ainsi qu'au moins un liquide (24) à évacuer. Cette enceinte (14) comprend au moins un orifice positionné au niveau de sa partie inférieure (22) ainsi qu'un système d'évacuation de...

The invention relates to a system for recovering (1) gaseous dihydrogen produced in a distribution pipe (11) arranged between a main reservoir (10) and a dihydrogen consuming device (19), the distribution pipe (11) comprising a pump (13). The system compri...

L'invention concerne un système d'alimentation (250) pour un aéronef arrangé entre deux réservoirs (110a-b) de dihydrogène et un moteur (106). Le système d'alimentation (250) comporte un module d'alimentation (249) qui assure l'écoulement du dihydro...

A hydrogen-fuelled aircraft power system (300) incorporates a gas turbine engine (301) and a fuel cell (302), in which air supply and cooling of the fuel cell (302) is integrated with the gas turbine engine (301) to improve overall efficiency of the power ...

The invention relates to a module (200) between a dihydrogen reservoir (110) and an engine (106) and comprises an outer chamber (202) and an inner chamber (204), a pipe line (206) between the reservoir (110) and the engine (106) through the chambers (202, ...

A propulsive aircraft gas turbine engine (103) comprises a turbine (208, 209) disposed in a gas turbine engine core (201) flow and a recuperator heat exchanger (218) disposed downstream of the turbine (208, 209) in gas turbine engine core flow, the recuper...