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.)

1. A gas turbine engine, the gas turbine engine comprising:

a bypass duct cover;

an engine core enclosure defining an engine core inlet;

a bypass fan; and

a plurality of outlet guide vanes extending between a radially inner surface of the bypass duct cover and a radially outer surface of the engine core outer casing to define an outlet guide vane span, the outlet guide vanes configured to support the engine core outer casing relative to the bypass duct cover;

wherein the bypass fan and engine core inlet define a bypass ratio of between 10 and 17; and the ratio of the outlet guide vane span to the bypass fan radius is between 0.45 and 0.55.

2. The gas turbine engine of claim 1, wherein at least one of the fan outlet guide vanes, the bypass duct shroud, and the bypass fan are arranged such that conditions areIs satisfied, wherein SPAN is_OGVFor the span of the outlet guide vane, CHORD_OGVIs the chord of the outlet guide vane, Xa is the distance between the center of the inlet aerodynamic pressure of the bypass nacelle and the center of the outlet guide vane, F_iFor the maximum certified intake air charge of the engine, R_OGVIs the engine axis distance of the tip of the outlet guide vane in the radial plane, K is a proportionality constant taking into account the young's modulus of the OGV, and x is the OGV tip deflection, where x is between 20mm and-20 mm.

3. The gas turbine engine of claim 1, wherein a ratio of an inner radius of the outlet guide vane to an outer radius of the outlet guide vane is between 0.4 and 0.6.

4. The gas turbine engine of claim 3, wherein a ratio of an inner radius of the outlet guide vane to an outer radius of the outlet guide vane is between 0.5 and 0.55.

5. The gas turbine engine of claim 1, wherein a ratio of an axial distance between an inlet of the bypass duct shroud and an intermediate chord of the outlet guide vane at the tip to an outer radius of the outlet guide vane is between 1 and 1.8.

6. The gas turbine engine of claim 5, wherein the ratio of the axial distance between the inlet of the bypass duct shroud and the intermediate chord of the outlet guide vane at the tip to the outer radius of the outlet guide vane is between 1.4 and 1.7.

7. The gas turbine engine of claim 1, wherein each outlet guide vane has an aspect ratio of between 2 and 8.

Example 1

The first engine is designed to provide between 75000 pounds of thrust and 85000 pounds of thrust at maximum static flat rated takeoff thrust. The engine has an engine speed of about 50: 1 and a total pressure ratio of 15: a bypass ratio of 1. The engine is a dual spool, geared design with a low pressure compressor, a high pressure compressor, and a high pressure turbine and a low pressure turbine coupled to a fan through a reduction gearbox).

In the engine, the outlet guide vane span (OGV)_SPAN) And bypass fan radius (R)_FAN) Is about 0.54. Thus, a high bypass ratio is provided, while also providing a relatively short OGV, resulting in a relatively robust, lightweight engine.

For this engine, the ratio of the inner radius of the outlet guide vane to the outer radius of the outlet guide vane is 0.5.

For this engine, the ratio of the axial distance between the intermediate chords of the inlet and outlet guide vanes of the bypass duct shroud at the tip to the outer radius of the outlet guide vane is 1.5. If a longer fan inlet is used, the ratio may be increased to about 1.7.