CRYOGENIC COOLING SYSTEM FOR AN AIRCRAFT

A gas turbine engine (20) comprises a compressor section (24) and a turbine section (28) operably coupled to the compressor section (24). It furthermore comprises means for selectively releasing a cooling fluid flow produced at a cryogenic temperature, and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section (24) and the turbine section (28).