A fuel conditioning system configured to supply an aircraft turbine engine with fuel from a cryogenic tank. The fuel circuit comprising a buffer tank for supplying the turbine engine and a plurality of compression modules configured to supply the buffer tank, each compression module comprising an elementary tank of fixed volume, an elementary heat source configured to increase the temperature of the fuel in the elementary tank in an isochoric manner, an inlet valve connecting the elementary tank to an upstream part of the fuel circuit, an outlet valve connecting the elementary tank to the buffer tank, and a venting valve connecting the elementary tank to the cryogenic tank via a return circuit in which a gaseous stream circulates.
Fuel conditioning system and method configured to supply an aircraft turbine engine with fuel from a cryogenic tank
2024-12-10
Patent
Electronic Resource
English
European Patent Office | 2024
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