Cryogenic fuel system and method for delivering fuel in an aircraft
AssigneeGeneral Electric Company
InventorsDeepak Manohar Kamath, Todd James Buchholz, Mehdi Milani Baladi, Michael Jay Epstein
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Abstract
A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine.
Claims19
A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, comprising:
- a cryogenic fuel stored in a tank;
- a supply line operably coupling the tank to the combustion chamber;
- a first pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump;
- and
- a second pump fluidly coupling the tank to the first pump to pre-pressurize the cryogenic fuel delivered to the first pump.
A method for delivering cryogenic fuel in a fuel system to a turbine engine having a combustion section and a compressor section, comprising:
- pressurizing the cryogenic fuel provided to the combustion section of the turbine engine utilizing a turbopump driven by the compressor to discharge pressure from the turbine engine, and
- pressurizing the cryogenic fuel with a second fuel pump before said cryogenic fuel is pressurized by the turbopump.
Dependencies are inferred from the claim text.