An exhaust duct for a turbine engine is provided including a duct having a generally hollow interior configured to receive a primary flow from a turbine section of the turbine engine and an ejector cooling air flow from an ejector of the turbine engine. The duct has a first end arranged in a first plane and a second end arranged in a second, distinct plane. The first plane and the second plane are arranged at an angle to one another between 70 degrees and 110 degrees.


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    Title :

    HIGH TURNING ANGLE EJECTOR COOLED TURBINE ENGINE EXHAUST DUCT


    Contributors:

    Publication date :

    2016-09-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / 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



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