A method of operating a gas turbine engine includes generating a flow of combustion products from a gas turbine generator that has a gas generator axis of rotation. A duct is oriented in a first position to direct the flow of combustion products that have passed over at least one gas generator turbine rotor through a fan drive turbine in response to a first desired flight condition. An axis of rotation of the fan drive turbine is transverse to a gas generator axis of rotation. The duct is oriented in a second position to direct the flow of combustion products that have passed over at least one gas generator turbine rotor through an augmentor section in response to a second desired flight condition.


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    Title :

    Gas turbine engine with selective flow path


    Contributors:

    Publication date :

    2020-02-18


    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




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