A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end.


    Access

    Download


    Export, share and cite



    Title :

    Bifurcated air inlet housing for a miniature gas turbine engine


    Contributors:

    Publication date :

    2020-05-05


    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



    GAS TURBINE ENGINE HAVING A BIFURCATED AIR INLET HOUSING

    JONES ANTHONY C / LYDON PATRICK M / THAYALAKHANDAN NAGAMANY et al. | European Patent Office | 2019

    Free access

    Bifurcated inlet scoop for gas turbine engine

    JEN HSIANMIN / LOSYEV SERGEY | European Patent Office | 2019

    Free access

    BIFURCATED INLET SCOOP FOR GAS TURBINE ENGINE

    JEN HSIANMIN / LOSYEV SERGEY | European Patent Office | 2020

    Free access

    AIRCRAFT WITH BIFURCATED AIR INLET

    IVANS STEVEN RAY / HAWTHORNE DAVID ALAN / HENSON BRAD ROBERT et al. | European Patent Office | 2021

    Free access

    Design and development of a compact bifurcated turboprop inlet

    BARTA, A. / BENNETT, W. / VITTAL, B. et al. | AIAA | 1991