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.
Cryogenic fuel system and method for delivering fuel in an aircraft
2018-04-03
Patent
Electronic Resource
English
Aircraft cryogenic fuel system design issues
AIAA | 1993
|CRYOGENIC FUEL SYSTEM AND METHOD FOR DELIERING FUEL IN AN AIRCRAFT
European Patent Office | 2015
|