A gas turbine engine comprising an interior zone 104 defined between a fairing 50 and a casing 52, wherein the gas turbine engine further comprises a zone ventilation arrangement comprising an inlet 102 through the fairing providing fluid communication between an area outside the fairing and the interior zone. There is an outlet 108 in fluid communication with the interior zone. There is an air amplifier 106 disposed within the interior zone. The air amplifier may be a coanda effect air amplifier or a fan type air amplifier. The air amplifier may be positioned or oriented to direct an air flow over a component of control hardware within the zone; the control hardware may be a valve, an actuator, or a component of an electric, fuel or oil system of an aircraft. The air amplifier may be powered by an air flow from the bypass duct (22, fig 1) or by a compressed air flow from a source of compressed air. The source of compressed air may be from a compressor (14, fig 1). There may be a valve 116 to control the flow of compressed air into the air amplifier.


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    Title :

    Zone ventilation arrangement


    Contributors:

    Publication date :

    2021-11-17


    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



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