PROBLEM TO BE SOLVED: To provide an exhaust nozzle of a turbine engine reduced in weight and improved in performance.SOLUTION: A nozzle of a turbine engine 102 includes a main outer wall extended from a core region of the engine 102 to an annular wall terminal end portion surrounding a tail cone of the engine to form a core nozzle 114, and a single engine core cowl 106 extended from the core region of the engine to an annular cowl terminal end portion to form a core compartment exhaust nozzle 116. The core compartment exhaust nozzle 116 discharges the air from the core compartment at a rear edge between the single engine core cowl 106 and the main outer side wall 108.SELECTED DRAWING: Figure 2B

    【課題】重量が低減され性能が高められたタービンエンジンの排気ノズルを提供する。【解決手段】タービンエンジン102のノズルは、エンジン102のコア領域からエンジンのテールコーンを取り囲む環状壁終端部まで延在し、コアノズル114を形成する主要な外側壁を含み、エンジンのコア領域から環状カウル終端部まで延在しコアコンパートメント排気ノズル116を形成し、シングルエンジンコアカウル106を含む。コアコンパートメント排気ノズル116は、シングルエンジンコアカウル106と主要な外側壁108との間の後縁においてコアコンパートメントからの空気を排出する。【選択図】図2B


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    Title :

    REAR EDGE CORE COMPARTMENT EXHAUST PORT OF AIRCRAFT ENGINE


    Additional title:

    航空エンジンの後縁コアコンパートメント排気口


    Contributors:

    Publication date :

    2017-06-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / 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 / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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