PROBLEM TO BE SOLVED: To mitigate one or more issues of flow inlets of an aircraft engine.SOLUTION: A flow inlet 10 formed on an interior surface of a cowl 28. The flow inlet has a supersonic compression section attached to a subsonic diffusion section at a throat. The supersonic compression section includes an at least partially elliptical compression ramp 30 which extends along an approximately 180 degree arc along the interior surface. The flow inlet may form part of an aircraft. A method of an air flow using the flow inlet is also disclosed.SELECTED DRAWING: Figure 2

    【課題】航空機エンジンの吸気口の一又は複数の問題を改善する。【解決手段】吸気口10はカウル28の内面に形成される。吸気口は、スロートにおいて亜音速拡散セクションに取り付けられた超音速圧縮セクションを有する。超音速圧縮セクションは、内面に沿った約180度の弧に沿って伸びる少なくとも部分的に楕円形の圧縮ランプ30を含む。吸気口は航空機の一部を形成し得る。当該吸気口を用いた気流の方法も開示される。【選択図】図2


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    Title :

    FLOW INLET


    Additional title:

    吸気口


    Contributors:

    Publication date :

    2016-11-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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