Methods and systems for starting hydrogen powered gas generators
Aircraft hydrogen fuel systems and methods and systems of starting such systems are described. The aircraft hydrogen fuel systems include a hydrogen burning main engine, a main tank configured to contain liquid hydrogen to be supplied to the main engine during a normal operation, and a starter tank configured to contain gaseous hydrogen to be used during a startup operation of the main engine. Methods and processes for starting and/or restarting such systems are described.
1. An aircraft hydrogen fuel system, comprising:
a hydrogen burning main engine;
a main tank configured to contain a first supply of hydrogen comprising liquid hydrogen, the first supply of hydrogen to be supplied to the main engine during a normal operation of the main engine;
a starter tank configured to contain a second supply of hydrogen comprising gaseous hydrogen, the second supply of hydrogen to be supplied to and consumed by the main engine during a startup operation of the main engine, wherein the starter tank is refillable from a ground source and wherein the gaseous hydrogen in the starter tank is at least partially formed by a gaseous hydrogen that is sourced from boil-off from the liquid hydrogen of the main tank;
an accumulator arranged between the main tank and the starter tank, the accumulator configured to accumulate the gaseous hydrogen from the boil-off; and
a pump configured to boost a pressure of the gaseous hydrogen from the boil-off prior to the boil-off being supplied into the starter tank.
2. The aircraft hydrogen fuel system of claim 1 , wherein the starter tank is manually exchangeable.
3. The aircraft hydrogen fuel system of claim 1 , wherein the main engine generates waste heat during the normal operation of the main engine and the waste heat is used within a main engine fuel conditioning heat exchanger to convert the liquid hydrogen from the main tank to a gaseous state of hydrogen during the normal operation of the main engine.
4. The aircraft hydrogen fuel system of claim 1 , further comprising an auxiliary power unit configured to heat the liquid hydrogen from the main tank to generate a gaseous form of hydrogen, a first portion of which is to be supplied to the main engine, wherein the auxiliary power unit (“APU”) includes an APU fuel conditioning heat exchanger.
5. The aircraft hydrogen fuel system of claim 4 , wherein the auxiliary power unit is a hydrogen burning unit.
6. The aircraft hydrogen fuel system of claim 4 , wherein the starter tank is configured to supply the gaseous hydrogen in the starter tank to the auxiliary power unit during a startup operation of the auxiliary power unit and waste heat of the started auxiliary power unit is used to heat the liquid hydrogen from the main tank to generate the gaseous form of hydrogen, of which the first portion is to be supplied to the main engine during the normal operation of the main engine.
7. The aircraft hydrogen fuel system of claim 5 , wherein the auxiliary power unit is supplied with the gaseous hydrogen from the starter tank during a startup operation of the auxiliary power unit.
8. The aircraft hydrogen fuel system of claim 5 , wherein a waste heat of the auxiliary power unit is used to convert the liquid hydrogen from the main tank to the gaseous form of hydrogen, wherein the auxiliary power unit is supplied with a second portion of the gaseous form of hydrogen converted from the liquid hydrogen that is sourced from the main tank during a normal operation of the auxiliary power unit.
9. The aircraft hydrogen fuel system of claim 1 , wherein the gaseous hydrogen from the starter tank is supplied to the main engine to perform a restart operation of the main engine in the event of a flame-out occurrence in the main engine.
10. The aircraft hydrogen fuel system of claim 1 , further comprising a valve arranged along a hydrogen flow path between the main tank and the main engine.
11. The aircraft hydrogen fuel system of claim 1 , wherein the main engine includes a compressor section, a combustor section having a burner, and a turbine section, wherein the combustor is configured to burn hydrogen fuel.
12. An aircraft hydrogen fuel system, comprising:
a hydrogen burning main engine;
a main tank configured to contain a first supply of hydrogen comprising liquid hydrogen, the first supply of hydrogen to be supplied to the main engine during a normal operation of the main engine;
a starter tank configured to contain a second supply of hydrogen comprising gaseous hydrogen, the second supply of hydrogen to be supplied to and consumed by the main engine during a startup operation of the main engine;
an accumulator arranged between the main tank and the starter tank, the accumulator configured to receive boil-off hydrogen from the liquid hydrogen in the main tank; and
a pump arranged between the accumulator and the starter tank, the pump configured to boost a pressure of the boil-off hydrogen from the main tank prior to the boil-off hydrogen being supplied into the starter tank.
13. The aircraft hydrogen fuel system of claim 12 , further comprising an auxiliary power unit configured to heat the liquid hydrogen from the main tank to generate a gaseous form of hydrogen, a first portion of which is to be supplied to the main engine, wherein the auxiliary power unit (“APU”) includes an APU fuel conditioning heat exchanger.
14. The aircraft hydrogen fuel system of claim 13 , wherein the auxiliary power unit is a hydrogen burning unit.
15. The aircraft hydrogen fuel system of claim 14 , wherein the auxiliary power unit is supplied with the gaseous hydrogen from the starter tank during a startup operation of the auxiliary power unit.
16. The aircraft hydrogen fuel system of claim 14 , wherein a waste heat of the auxiliary power unit is used to convert the liquid hydrogen from the main tank to the gaseous form of hydrogen, wherein the auxiliary power unit is supplied with a second portion of the gaseous form of hydrogen from the main tank during a normal operation of the auxiliary power unit.