CPC F02C 7/224 (2013.01) [F02C 3/22 (2013.01); F02C 7/232 (2013.01); F02C 7/26 (2013.01); F02C 7/262 (2013.01); F02C 7/32 (2013.01); F02C 9/40 (2013.01); B64D 37/04 (2013.01); B64D 37/06 (2013.01); B64D 37/10 (2013.01); B64D 37/14 (2013.01); B64D 37/16 (2013.01); B64D 37/30 (2013.01); B64D 37/34 (2013.01); B64F 1/28 (2013.01); F05D 2220/323 (2013.01); F05D 2240/36 (2013.01)] | 16 Claims |
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.
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