GAS TURBINE ENGINE FUEL SYSTEM

Abstract: a fuel system () for a gas turbine engine (). the fuel system comprises a fuel offtake () configured to divert a portion of hydrogen fuel from a main fuel conduit (), a burner () configured to burn the portion of hydrogen fuel diverted from the main fuel conduit () and at least first and second heat exchangers (). the first heat exchanger () is configured to transfer heat from exhaust gasses produced by the burner () to hydrogen fuel in the main fuel conduit () and the second heat exchanger () is provided upstream in hydrogen flow of the first heat exchanger () and is configured to transfer heat from a further heat exchange fluid to hydrogen fuel in the main fuel conduit (). in an embodiment, the further heat exchange fluid is compressor bleed air bled from a core compressor of the gas turbine engine.

Inventor(s): John E RIMMER, Murthy V V S Ravikanti, Thomas A. Chin

CPC Classification: F23R3/005 (Continuous combustion chambers using liquid or gaseous fuel)

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