CPC F02C 7/224 (2013.01) [F02C 3/20 (2013.01); F02C 3/22 (2013.01); F02C 7/04 (2013.01); F02C 7/14 (2013.01); F02C 7/143 (2013.01); F02C 7/18 (2013.01); F02C 7/22 (2013.01); F02C 7/222 (2013.01); F23R 3/04 (2013.01); F23R 3/286 (2013.01); F02C 9/40 (2013.01); F05D 2220/32 (2013.01); F05D 2240/35 (2013.01)] | 19 Claims |
1. A complex cycle gas turbine engine for an aircraft with hydrogen fuel supply, comprising:
in fluid flow series, a core gas turbine and a recuperator for heating hydrogen fuel prior to combustion by turbine exhaust products; and
a fuel delivery system for delivering the hydrogen fuel from a cryogenic storage system to the recuperator, the fuel delivery system including a pump, a metering device, and a fuel heating system for heating the hydrogen fuel,
wherein the metering device comprises a sonic fixed orifice configured to operate in a choked condition and a flow rate is controlled by adjusting pressure delivered by the pump upstream of the sonic fixed orifice based on a measured upstream temperature of the sonic fixed orifice and an area of the sonic fixed orifice,
the fuel heating system comprises a vaporiser configured to vaporise liquid hydrogen from the cryogenic storage system, and
the vaporiser comprises a fuel offtake for diverting a portion of the hydrogen fuel from a fuel conduit for combustion in a burner located in heat exchange relationship with the fuel conduit.
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