An exhaust section for an aircraft gas turbine engine includes an exhaust nozzle in a downstream serial flow relationship with the gas turbine engine having a fan section, a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section compresses intake air from the fan section, which is mixed with fuel and combusted into hot gases in the combustion section. The hot gases drive the turbines of the turbine section, and are expelled from the gas turbine engine at the exhaust section.


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    Title :

    EXHAUST SECTION FOR AN AIRCRAFT GAS TURBINE ENGINE


    Contributors:

    Publication date :

    2018-11-15


    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 / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES



    EXHAUST SECTION FOR AN AIRCRAFT GAS TURBINE ENGINE

    ENGELHARDT MICHEL | European Patent Office | 2015

    Free access

    EXHAUST SECTION FOR AN AIRCRAFT GAS TURBINE ENGINE

    ENGELHARDT MICHEL | European Patent Office | 2016

    Free access