To provide a turbine engine with a single wall cantilevered architecture.SOLUTION: An apparatus and method for mounting a turbine engine (20) to an aircraft (10) can include an engine core (40) for the turbine engine (20) including a compressor section (42), a combustor section (48), and a turbine section (52) in flow arrangement. At least one strut (110) couples to the engine core (40) at a single mount plane (120). A structural wall (116) at least partially defining a mainstream flow path (118) couples to the at least one strut (110) and passes through the compressor section (42) and the turbine section (52).SELECTED DRAWING: Figure 2

    【課題】単一壁片持ち構造を有するタービンエンジンを提供する。【解決手段】タービンエンジン(20)を航空機(10)に取り付けるための装置および方法が、圧縮機部分(42)と、燃焼器部分(48)と、タービン部分(52)とを流れの配置にて含むタービンエンジン(20)のためのエンジンコア(40)を含むことができる。少なくとも1つの支柱(110)が、単一の取り付け平面(120)においてエンジンコア(40)に結合する。主流路(118)を少なくとも部分的に定める構造壁(116)が、少なくとも1つの支柱(110)に結合し、圧縮機部分(42)およびタービン部分(52)を通過する。【選択図】図2


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    Title :

    TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE


    Additional title:

    単一壁片持ち構造を有するタービンエンジン



    Publication date :

    2019-03-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

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



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