A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel stabilization unit. The fuel-air heat exchanger places deoxygenized fuel in a heat exchange relationship with compressor bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine is operationally connected to the engine compressor and receives cooled bleed air from the fuel-air heat exchanger.


    Access

    Download


    Export, share and cite



    Title :

    Small engine cooled cooling air system



    Publication date :

    2017-02-28


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Small engine cooled cooling air system

    RHODEN WILLIAM E / JALBERT PETER L / BEAUPRE RUDOLPH THOMAS et al. | European Patent Office | 2018

    Free access

    External cooling system of water-cooled engine

    ZHOU ZHENFEI | European Patent Office | 2021

    Free access

    Development of Oil-Cooled Engine for Optimization of Engine Cooling System

    Kitayama, Amane / Tanaka, Koichi / Arase, Kunio | SAE Technical Papers | 2016


    Development of Oil-Cooled Engine for Optimization of Engine Cooling System

    Tanaka, Koichi / Arase, Kunio / Kitayama, Amane | British Library Conference Proceedings | 2016


    Gas turbine engine in-board cooled cooling air system

    LO CHARLES | European Patent Office | 2019

    Free access