PROBLEM TO BE SOLVED: To provide a system for improving efficiency of an engine by cancelling influence of the drag on an aircraft, including the skin friction drag, the form drag and the induced drag.SOLUTION: An aircraft (10) including a fuselage (20) and an aft engine (200) is provided. The fuselage extends from a forward end (14) of the aircraft towards an aft end (16) of the aircraft. The aft engine is installed in the fuselage proximately to the aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine, the fan including a plurality of fan blades. The aft engine also includes a nacelle surrounding the plurality of fan blades and defining an inlet. The inlet defines a non-axis symmetric shape with respect to the central axis of the aft engine to, e.g., allow a maximum amount of air to flow into the aft engine.SELECTED DRAWING: Figure 1

    【課題】表面摩擦抗力、形状抗力、および誘導抗力を含む航空機への抗力の影響を相殺し、エンジンの効率を改善するためのシステムを提案する。【解決手段】胴体(20)および後部エンジン(200)を含む航空機(10)が提供される。胴体は、航空機の前方端(14)から航空機の後方端(16)に向かって延在する。後部エンジンは、航空機の後方端に近接して胴体に取り付けられる。後部エンジンは、後部エンジンの中心軸の周りに回転可能で複数のファンブレードを含むファンを含む。後部エンジンはまた、複数のファンブレードを取り囲み、入口を定めるナセルを含む。入口は、後部エンジンの中心軸に対して非軸対称形を定めて、例えば、後部エンジンに最大限の空気流量が入ることを可能にする。【選択図】図1


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    Title :

    NON-AXIS SYMMETRIC AFT ENGINE


    Additional title:

    非軸対称後部エンジン


    Contributors:

    Publication date :

    2017-03-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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