Abstract: A gas delivery system intended for use in delivering hydrogen gas from a cryogenic liquid hydrogen storage tank is provided. The gas delivery system has: a cryogenic liquid storage tank; an evaporator; a pressurisable gas reservoir; a valve sub-system including: a multi-outlet valve arrangement having a first valve inlet, a first valve outlet and a second valve outlet; and a multi-inlet valve arrangement having a second valve inlet, a third valve inlet and a third valve outlet; a delivery line connected to the third valve outlet; an evaporator feed line connecting the storage tank and the evaporator inlet; an evaporator dispensing line connecting the evaporator and the first valve inlet; a reservoir feed line connecting the first valve outlet and the reservoir; a reservoir dispensing line connecting the reservoir and the second valve inlet; and a reservoir bypass line connecting the second valve outlet and the third valve inlet.

Abstract: An aircraft propulsion system comprises a gas turbine engine arranged to provide propulsive thrust and a fuel cell system having an air input port, the aircraft propulsion system being configured such that air from a compressor of the gas turbine engine is provided to the air input port during operation of the aircraft propulsion system. The fuel cell system is able to provide appreciable electrical power at altitude without the need for a dedicated compressor.

Abstract: A hydrogen storage tank has a composite laminate wall, a hydrogen-porous layer in contact with the outer surface of the composite laminate wall and a hydrogen-non-porous layer in contact with the outer surface of the hydrogen-porous layer, the hydrogen-non-porous layer having an output port for venting hydrogen which passes through the composite laminate wall and the hydrogen-porous layer from the interior of the tank. The tank allows hydrogen which leaks through the composite laminate wall to be collected and re-used. The invention also allows for the rate of hydrogen leakage from the tank to be measured, providing a measure of the structural integrity of the tank.

Abstract: A reformer module (10) comprises a hollow support member (12) having at least one passage (14) extending longitudinally therethrough. The hollow support member (14) has an external surface (20), a barrier layer (22) arranged on at least a portion of the external surface (20) of the hollow support member (12), a catalyst layer (24) arranged on the barrier layer (22) and a sealing layer (26) arranged on the catalyst layer (24) and the external surface (20) of the hollow support member (12) other than the at least a portion of the external surface of the hollow support member (12). By providing the barrier layer (22) and the catalyst layer (24) on the exterior surface (20) of the hollow support member (12), the distribution of the barrier layer (22) and/or the catalyst layer (24) may be more precisely controlled and thus a non-uniform distribution of barrier layer (22) and/or catalyst layer (24) may be achieved.

Abstract: A reformer module (10) comprises a hollow support member (12) having at least one passage (14) extending longitudinally therethrough. The hollow support member (14) has an external surface (20), a barrier layer (22) arranged on at least a portion of the external surface (20) of the hollow support member (12), a catalyst layer (24) arranged on the barrier layer (22) and a sealing layer (26) arranged on the catalyst layer (24) and the external surface (20) of the hollow support member (12) other than the at least a portion of the external surface of the hollow support member (12). By providing the barrier layer (22) and the catalyst layer (24) on the exterior surface (20) of the hollow support member (12), the distribution of the barrier layer (22) and/or the catalyst layer (24) may be more precisely controlled and thus a non-uniform distribution of barrier layer (22) and/or catalyst layer (24) may be achieved.

Abstract: A reformer module (10) comprises a hollow support member (12) having at least one passage (14) extending longitudinally therethrough. The hollow support member (14) has an external surface (20), a barrier layer (22) arranged on at least a portion of the external surface (20) of the hollow support member (12), a catalyst layer (24) arranged on the barrier layer (22) and a sealing layer (26) arranged on the catalyst layer (24) and the external surface (20) of the hollow support member (12) other than the at least a portion of the external surface of the hollow support member (12). By providing the barrier layer (22) and the catalyst layer (24) on the exterior surface (20) of the hollow support member (12), the distribution of the barrier layer (22) and/or the catalyst layer (24) may be more precisely controlled and thus a non-uniform distribution of barrier layer (22) and/or catalyst layer (24) may be achieved.

Abstract: A gas turbine engine (10) combustion chamber (28) comprises a primary combustion zone (36) and a secondary combustion zone(40) in which lean mixtures of fuel and air are burned. Air is supplied to a first mixing duct (50) through a swirler (52). Air is supplied to an additional mixing duct (58) through a swirler (54) and hydrocarbon fuel is supplied to the additional mixing duct (58) through a swirler (66). The hydrocarbon fuel and air is mixed and reacted in a catalytic partial oxidation reaction zone (60) which produces a product gas comprising a mixture of hydrogen, carbon monoxide, carbon dioxide, water and unreacted hydrocarbon fuel. Additional hydrocarbon fuel is supplied from apertures (72) and is mixed with the product gas in a mixing chamber (68) and this mixture is supplied to the first mixing duct (50) and mixes with the air. The first mixing duct (50) supplies a lean mixture of fuel into the primary combustion zone (36).