Propulsion system comprising a hydrogen-burning gas turbine engine
A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.
1 . A propulsion system comprising:
(i) a propulsive, hydrogen-burning gas turbine engine;
(ii) a first tank arranged to store liquid hydrogen with an ullage;
(iii) a first fuel line arranged to convey the liquid hydrogen from the first tank to a combustion apparatus of the propulsive, hydrogen-burning gas turbine engine, the first fuel line including a fuel pump and a vaporiser,
wherein the fuel pump is arranged to transport the liquid hydrogen from the first tank to the vaporiser and the vaporiser is arranged to vaporise the liquid hydrogen utilising heat from the propulsive, hydrogen-burning gas turbine engine and provide resulting gaseous hydrogen to the combustion apparatus of the propulsive, hydrogen-burning gas turbine engine and wherein the propulsion system further comprises:
(iv) a second tank arranged to store compressed gaseous hydrogen;
(v) a second fuel line arranged to convey the compressed gaseous hydrogen between the second tank and the first fuel line at a position thereon intermediate the vaporiser and the combustion apparatus; and
(vi) a duct which in operation of the propulsion system connects the compressed gaseous hydrogen stored in the second tank to the ullage of the first tank, and wherein
the first tank and a portion of the first fuel line extending from the first tank to the vaporiser are contained within a first volume which is arranged for evacuation during operation of the fuel system, and
the propulsion system further comprises a fuel cell stack and a third fuel line arranged to convey the compressed gaseous hydrogen from the second tank to the fuel cell stack and an electric vacuum pump arranged to receive electrical power from the fuel cell stack and substantially evacuate the first volume.
2 . The propulsion system according to claim 1 wherein the fuel pump is an electric pump and the fuel cell stack is arranged to provide the electrical power to the fuel pump.
3 . The propulsion system according to claim 1 wherein the fuel cell stack is arranged to provide the electrical power to an electric starter-motor comprised in the propulsive, hydrogen-burning gas turbine engine.
4 . The propulsion system according to claim 3 wherein the fuel pump is an electric pump and the fuel cell stack is arranged to provide the electrical power to the fuel pump.
5 . The propulsion system according to claim 1 wherein:
(i) the fuel pump is an electric pump and the fuel cell stack is arranged to provide the electrical power to the fuel pump; and/or
(ii) the fuel cell stack is arranged to provide electrical power to an electric starter motor comprised in the propulsive, hydrogen-burning gas turbine engine.
6 . The propulsion system according to claim 1 further comprising an apparatus for maintaining an inert atmosphere within a second volume which includes a portion of the first fuel line including the vaporiser.
7 . The propulsion system according to claim 6 wherein said apparatus comprises a third tank arranged to store compressed gaseous nitrogen and a duct coupling the third tank to said second volume.
8 . The propulsion system according to claim 7 further comprising an apparatus arranged to selectively convey the compressed gaseous hydrogen from the second tank and the compressed gaseous nitrogen from the third tank to the first fuel line at a position thereon between the first tank and the fuel pump.
9 . The propulsion system according to claim 1 further comprising a third tank arranged to store gaseous nitrogen and an apparatus arranged to selectively convey the compressed gaseous hydrogen from the second tank and the gaseous nitrogen from the third tank to the first fuel line at a position thereon between the first tank and the fuel pump.
10 . The propulsion system according to claim 1 further comprising an electrical power distribution system, the fuel cell stack being arranged to provide the electrical power to the electrical power distribution system.
11 . The propulsion system according to claim 1 wherein the vaporiser comprises a heat exchanger arranged to receive compressor bleed air from the propulsive, hydrogen-burning gas turbine engine and transmit heat from the compressor bleed air to the liquid hydrogen within the first fuel line.
12 . The propulsion system according to claim 1 wherein the vaporiser comprises a heat-exchanger arranged to transmit heat from oil within an oil system of the propulsive, gas turbine engine to the liquid hydrogen within the first fuel line.
13 . The propulsion system according to claim 1 wherein the vaporiser comprises a heat-exchanger arranged to transmit heat from an exhaust flow of the propulsive, gas turbine engine to the liquid hydrogen within the first fuel line.
14 . An aircraft comprising the propulsion system according to claim 1 .
15 . The aircraft according to claim 14 wherein the aircraft is an aeroplane or a helicopter.