CPC F02C 3/20 (2013.01) [F02C 7/224 (2013.01); F02C 6/20 (2013.01); F02C 7/14 (2013.01); F02C 9/36 (2013.01); F02C 9/40 (2013.01)] | 20 Claims |
1. A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel-topped with a boil-off gas and including a high-pressure liquid pump connected to an outlet of said cryogenic reservoir and intended to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator and producing heat via its exhaust gases, a gas compressor mounted between the cryogenic reservoir and the auxiliary turbomachine to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting an outlet of the gas compressor to an inlet of the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, said electric generator supplying electrical energy to said high-pressure liquid pump and said gas compressor.
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