A gas turbine engine includes a compressor section in series flow with a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines, the compressor section and turbine section together defining a core air flowpath. A sump is positioned inward of the core air flowpath for containing and collecting lubrication oil. Additionally, a heat exchanger is positioned in direct thermal communication with the sump for removing heat from lubrication oil contained therein to reduce a size and/or amount of heat exchangers located radially outward of the core air flowpath.


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    Title :

    GAS TURBINE ENGINE SUMP HEAT EXCHANGER


    Additional title:

    ECHANGEUR DE CHALEUR DE CARTER DE MOTEUR DE TURBINE A GAZ



    Publication date :

    2017-04-30


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F16N LUBRICATING , Schmierung



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