A gas turbine engine component includes a heat exchange structure (96) having an upstream end and a downstream end. A diffusing duct (68) is associated with the upstream end. A throttle member (102) controls air flow through the heat exchange structure (96), wherein the throttle member (102) has a non-circular cross section and is mounted to the downstream end of the heat exchange structure (96) or is mounted between the upstream end and the diffusing duct (68).


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    Title :

    HEAT EXCHANGER FOR GAS TURBINE ENGINE


    Additional title:

    WÄRMETAUSCHER FÜR GASTURBINENTRIEBWERK
    ECHANGEUR DE CHALEUR POUR MOTEUR À TURBINE À GAZ


    Contributors:

    Publication date :

    2019-08-21


    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



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