A cooling system for an aircraft capable of travelling at hypersonic speeds includes an inlet (22) configured to receive a first medium and a thermodynamic device (24) fluidly connected to the inlet (22). The thermodynamic device (24) includes at least one turbine and a compressor operably coupled via a shaft. An outlet of the at least one turbine is directly fluidly connected to an inlet of the compressor. An electric generator (34) is operably coupled to the at least one turbine.
ULTRA-HIGH TEMPERATURE TURBO GENERATOR
ULTRAHOCHTEMPERATURTURBOGENERATOR
TURBOGÉNÉRATEUR À ULTRA-HAUTE TEMPÉRATURE
2025-02-12
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |