A gas turbine engine de-icing system includes a heat exchanger (64). A coolant loop (92) is in fluid communication with the heat exchanger (64) and is configured to circulate a coolant. An engine oil loop (91) is in fluid communication with the heat exchanger (64) and is configured to transfer heat to the coolant. A gas turbine engine inlet structure (92) includes a cavity (102). A manifold (98) is arranged in the cavity (102) and is in fluid communication with the coolant loop (92). The manifold (98) is configured to spray the coolant onto the gas turbine engine inlet structure (62) to de-ice the gas turbine engine inlet structure (62).


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    Title :

    GAS TURBINE ENGINE NACELLE ANTI-ICING SYSTEM


    Additional title:

    ENTEISUNGSSYSTEM FÜR GASTURBINENMOTORGONDEL
    SYSTÈME ANTIGIVRAGE DE NACELLE DE MOTEUR À TURBINE À GAZ


    Contributors:

    Publication date :

    2018-10-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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