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公开(公告)号：EP2944767B1
公开(公告)日：2018-09-12
申请号：EP15164984.5
申请日：2015-04-24
申请人： Rolls-Royce plc
发明人： Bagall, Adam MacGregor , Beecroft, Peter , Stretton, Richard Geoffrey , Woodrow, Philip Geoffrey , Baralon, Stephane Michel Marcel , Smith, Angus Roy
CPC分类号： F02C9/18 , F01D9/02 , F01D9/065 , F01D25/24 , F02C6/08 , F02C7/14 , F02C7/18 , F02C7/185 , F02K3/06 , F02K3/115 , Y02T50/675
摘要： A gas turbine engine comprising an outlet guide vane and a bifurcation fairing is disclosed. The outlet guide vane is located in a bypass duct of the gas turbine engine downstream of a fan and is of aerofoil form. The bifurcation fairing traverses the radial extent of the bypass duct and has an upstream end that blends into a trailing edge of the outlet guide vane. The bifurcation fairing comprises a scoop protruding outwards from its side corresponding to a pressure side of the upstream outlet guide vane. The scoop comprises a forward facing inlet leading to a delivery conduit extending inside the bifurcation fairing for delivery in use of bypass air to one or more components of the gas turbine engine.
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公开(公告)号：EP2148064A2
公开(公告)日：2010-01-27
申请号：EP09251523.8
申请日：2009-06-09
申请人： Rolls-Royce plc
CPC分类号： F02C7/04 , B64D33/02 , F02C7/045 , F05D2240/14 , F05D2250/51 , F05D2250/70 , Y10T137/0536
摘要： A nacelle for a gas turbine engine has an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series, an intake lip and a diffuser. The diffuser has, also in flow series, a main diffuser section and an optional shorter straight wall diffuser section. The main diffuser section is bounded by an inner wall of the nacelle, the inner wall curving in the airflow direction of the engine. On each longitudinal section containing the engine axis, at the downstream end of the main diffuser section the inner wall has a non zero curvature. Thus each circumferential position on the inner wall at the downstream end of the main diffuser section has a curvature defined by a respective radius of curvature. However, one or more of the radii of curvature differ from the others of the radii of curvature.
摘要翻译： 用于燃气涡轮发动机的机舱在机舱的上游端处具有进气口并且在机舱的下游端处具有排气。 进气系列中有一个进气口和一个扩散器。 扩散器也具有流动系列，主扩散器部分和可选的较短直壁扩散器部分。 主扩散器部分由发动机舱的内壁界定，内壁在发动机的气流方向上弯曲。 在包含发动机轴线的每个纵向部分上，在主扩散器部分的下游端处，内壁具有非零曲率。 因此，主扩散器部分的下游端处的内壁上的每个圆周位置具有由相应的曲率半径限定的曲率。 然而，一个或多个曲率半径与曲率半径的其他曲率半径不同。
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公开(公告)号：EP2148062A2
公开(公告)日：2010-01-27
申请号：EP09251521.2
申请日：2009-06-09
申请人： Rolls-Royce plc
摘要： An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight. A method of designing a nacelle for a gas turbine engine includes the steps of:
defining such an initial geometry for the nacelle;
altering the shape and/or position of the highlight; and
obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the altered highlight to smoothly blend the altered highlight to unadjusted surfaces of the intake further removed from the altered highlight.摘要翻译： 机舱的初始几何形状在机舱的上游端处提供进气口并在机舱的下游端处提供排气。 进气系列中有一个进气口和一个扩散器。 进气唇缘具有限定进气唇缘的内表面和外表面之间的边界的突出部分。 在包含发动机轴线的所有纵向部分上（i）内部和外部曲面在高光部分处相切匹配，并且（ii）内部和外部曲面在高亮部分处具有其最大曲率。 一种设计用于燃气涡轮发动机的机舱的方法包括以下步骤：为机舱定义这样的初始几何形状; 改变高光的形状和/或位置; 以及通过调整与改变的突出部分相邻的吸入口的表面以获得改变的几何形状，以将改变的突出部分平滑地混合到进一步从改变的突出部分移除的未调整表面。
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公开(公告)号：EP2944767A1
公开(公告)日：2015-11-18
申请号：EP15164984.5
申请日：2015-04-24
申请人： Rolls-Royce plc
发明人： Bagnall, Adam , Beecroft, Peter , Stretton, Richard Geoffrey , Woodrow, Philip Geoffrey , Baralon, Stephane Michel Marcel , Smith, Angus Roy
CPC分类号： F02C9/18 , F01D9/02 , F01D9/065 , F01D25/24 , F02C6/08 , F02C7/14 , F02C7/18 , F02C7/185 , F02K3/06 , F02K3/115 , Y02T50/675
摘要： A gas turbine engine is disclosed comprising a bifurcation fairing located in a bypass duct of the gas turbine engine and traversing the radial extent of the bypass duct. The bifurcation fairing has a delivery conduit inlet leading to a delivery conduit extending inside the bifurcation fairing, the delivery conduit being arranged in use for delivery of bypass air to one or more components of the gas turbine engine. A diverter conduit has a diverter conduit inlet from the delivery conduit upstream of the delivery conduit reaching the one or more components of the gas turbine engine. The diverter conduit has an outlet to a location other than the one or more components of the gas turbine engine.
摘要翻译： 公开了一种燃气涡轮发动机，其包括位于燃气涡轮发动机的旁通管道中并横穿旁路管道的径向范围的分叉整流装置。 分岔整流罩具有通向在分岔整流装置内部延伸的输送导管的输送导管入口，输送导管被布置成用于将旁路空气输送到燃气涡轮发动机的一个或多个部件。 分流管道具有从输送导管上游的输送管道到达燃气涡轮发动机的一个或多个部件的分流管道入口。 分流管道具有除了燃气涡轮发动机的一个或多个部件之外的位置的出口。
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公开(公告)号：EP2148063A3
公开(公告)日：2014-03-19
申请号：EP09251522.0
申请日：2009-06-09
申请人： Rolls-Royce plc
摘要： An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight. A method of designing a nacelle for a gas turbine engine includes the steps of:
defining such an initial geometry for the nacelle;
pivoting, at each of one or more positions on the highlight and in the plane of the respective longitudinal section, the front portion of the section of intake lip lying in the respective longitudinal section about the highlight; and
obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion.-
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公开(公告)号：EP2148063A2
公开(公告)日：2010-01-27
申请号：EP09251522.0
申请日：2009-06-09
申请人： Rolls-Royce plc
摘要： An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight. A method of designing a nacelle for a gas turbine engine includes the steps of:
defining such an initial geometry for the nacelle;
pivoting, at each of one or more positions on the highlight and in the plane of the respective longitudinal section, the front portion of the section of intake lip lying in the respective longitudinal section about the highlight; and
obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion.摘要翻译： 机舱的初始几何形状提供在机舱的上游端的进气口和在机舱的下游端的排气口。 进气口具有进气口和扩散器。 进气唇缘具有突出部，其限定了进气口的内表面和外表面之间的边界。 在包含发动机轴线的所有纵向部分（i）上，内表面和外表面在高光处相切匹配，（ii）内表面和外表面在高亮处具有最大曲率。 设计燃气涡轮发动机的机舱的方法包括以下步骤：为机舱定义这样的初始几何形状; 在突出部分的一个或多个位置和相应纵向部分的平面中的每一个处枢转，位于相应纵向部分周围的突出部分的进气口部分的前部; 并且通过调节邻近枢转的前部的进气口的表面来获得改变的几何形状，以将枢转的前部的表面平滑地混合到进一步从转动的前部分移除的进气口的未调整的表面。
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公开(公告)号：EP2148063B1
公开(公告)日：2018-10-10
申请号：EP09251522.0
申请日：2009-06-09
申请人： Rolls-Royce plc
摘要： An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight. A method of designing a nacelle for a gas turbine engine includes the steps of: defining such an initial geometry for the nacelle; pivoting, at each of one or more positions on the highlight and in the plane of the respective longitudinal section, the front portion of the section of intake lip lying in the respective longitudinal section about the highlight; and obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion.
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公开(公告)号：EP2148062A3
公开(公告)日：2014-03-19
申请号：EP09251521.2
申请日：2009-06-09
申请人： Rolls-Royce plc
摘要： An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight. A method of designing a nacelle for a gas turbine engine includes the steps of:
defining such an initial geometry for the nacelle;
altering the shape and/or position of the highlight; and
obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the altered highlight to smoothly blend the altered highlight to unadjusted surfaces of the intake further removed from the altered highlight.-
公开(公告)号：EP2148064A3
公开(公告)日：2013-10-23
申请号：EP09251523.8
申请日：2009-06-09
申请人： Rolls-Royce plc
CPC分类号： F02C7/04 , B64D33/02 , F02C7/045 , F05D2240/14 , F05D2250/51 , F05D2250/70 , Y10T137/0536
摘要： A nacelle for a gas turbine engine has an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series, an intake lip and a diffuser. The diffuser has, also in flow series, a main diffuser section and an optional shorter straight wall diffuser section. The main diffuser section is bounded by an inner wall of the nacelle, the inner wall curving in the airflow direction of the engine. On each longitudinal section containing the engine axis, at the downstream end of the main diffuser section the inner wall has a non zero curvature. Thus each circumferential position on the inner wall at the downstream end of the main diffuser section has a curvature defined by a respective radius of curvature. However, one or more of the radii of curvature differ from the others of the radii of curvature.
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