A system (32) for managing thermal transfer in an aircraft includes a fuel stabilization unit (44), a fuel-air heat exchanger (50), and a turbine (60). The fuel-air heat exchanger (50) is located downstream from the fuel stabilization unit (44). The fuel-air heat exchanger (50) places deoxygenized fuel in a heat exchange relationship with compressor (58) bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine (60) is operationally connected to the engine compressor (58) and receives cooled bleed air from the fuel-air heat exchanger (50) to cool the turbine (60).
Small engine cooled cooling air system
Kleinmotorgekühltes Kühlluftsystem
Petit système de refroidissement d'air refroidi de moteur
2018-11-07
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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