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.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    HIGH TURNING ANGLE EJECTOR COOLED TURBINE ENGINE EXHAUST DUCT


    Beteiligte:

    Erscheinungsdatum :

    08.09.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    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



    INSTRUMENTED TURBINE EXHAUST DUCT

    LEFEBVRE GUY / SYNNOTT REMY / PAOLUCCI MICHAEL | Europäisches Patentamt | 2022

    Freier Zugriff

    GAS TURBINE ENGINE WITH EJECTOR

    KHALID SYED JALALUDDIN | Europäisches Patentamt | 2017

    Freier Zugriff

    TURBINE ENGINE SECONDARY EJECTOR SYSTEM

    LAMB JR DONALD W / BOWLES PATRICK ORMANDE | Europäisches Patentamt | 2021

    Freier Zugriff

    Turbine engine secondary ejector system

    LAMB JR DONALD W / BOWLES PATRICK ORMANDE | Europäisches Patentamt | 2023

    Freier Zugriff

    Exhaust ejector

    XU JIAXIN / GU SHUQING / XU LIANG et al. | Europäisches Patentamt | 2024

    Freier Zugriff