A turbine engine having an engine core, an inner cowl radially surrounding the engine core, an outer cowl radially surrounding the inner cowl and spaced from the inner cowl to form an annular passage between the inner and outer cowls that defines a nozzle, at least one control surface provided on the inner cowl and movable between a retracted position, where the nozzle has a first cross-sectional area, and an extended position where the nozzle has a second cross-sectional area that is less than the first cross-sectional area and an actuator operably coupled to the control surface and configured to move the control surface to control the cross-sectional area of the nozzle.


    Access

    Download


    Export, share and cite



    Title :

    TURBINE ENGINES WITH VARIABLE AREA NOZZLE


    Contributors:

    Publication date :

    2018-01-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



    Turbine engines with variable area nozzle

    HOWARTH GRAHAM FRANK / CALDER DAVID PATRICK | European Patent Office | 2020

    Free access

    Partially variable area turbine nozzle

    ANDERSEN, R. / HAUBERT, R. | AIAA | 1979


    Gas turbine engine with variable area fan nozzle

    HALL ANDRE M / KOHLENBERG GREGORY A / GILSON JONATHAN | European Patent Office | 2019

    Free access

    Gas turbine engine with axial movable fan variable area nozzle

    KOHLENBERG GREGORY A / ZAMORA SEAN P | European Patent Office | 2019

    Free access

    GAS TURBINE ENGINE WITH AXIAL MOVABLE FAN VARIABLE AREA NOZZLE

    KOHLENBERG GREGORY A / ZAMORA SEAN P | European Patent Office | 2018

    Free access