阅读说明：本技术 气体涡轮引擎安装布置结构 (Gas turbine engine mounting arrangement ) 是由 R.G.斯特雷顿 S.A.拉多姆斯基 于 2019-08-08 设计创作，主要内容包括：本公开题为“气体涡轮引擎安装布置结构”。气体涡轮引擎(10)包括旁路管道罩(21)、限定引擎核芯入口的引擎核芯外壳(22)、旁路风扇(13)和多个出口导向叶片(24)。每个出口导向叶片(24)在旁路管道护罩(21)的径向内表面和引擎核芯外壳(22,23)的径向外表面之间延伸以限定出口导向叶片跨度(SPANOGV)。该出口导向叶片(24)被构造成相对于旁路管道护罩(21)来支撑引擎核芯外壳(22,23)。该旁路风扇(13)和引擎核芯入口(34)限定介于10和17之间的旁路比,并且该出口导向叶片跨度(OGVSPAN)与旁路风扇半径(RFAN)的比率介于0.45和0.55之间。(The present disclosure is entitled "gas turbine engine mounting arrangement". The gas turbine engine (10) includes a bypass duct shroud (21), an engine core outer casing (22) defining an engine core inlet, a bypass fan (13), and a plurality of outlet guide vanes (24). Each outlet guide vane (24) extends between a radially inner surface of the bypass duct shroud (21) and a radially outer surface of the engine core casing (22, 23) to define an outlet guide vane span (sparnogv). The outlet guide vanes (24) are configured to support the engine core outer casing (22, 23) relative to the bypass duct shroud (21). The bypass fan (13) and the engine core inlet (34) define a bypass ratio of between 10 and 17, and a ratio of the Outlet Guide Vane Span (OGVSPAN) to the bypass fan Radius (RFAN) is between 0.45 and 0.55.)