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公开(公告)号：US07708520B2
公开(公告)日：2010-05-04
申请号：US11605678
申请日：2006-11-29
IPC分类号： F01D11/02
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/712
摘要： A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.
摘要翻译： 燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。 每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的凹槽相关联。 凹口袋及其相关的刀刃密封件产生一对涡流，防止泄漏到涡轮部分的径向内部。
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公开(公告)号：US20080124215A1
公开(公告)日：2008-05-29
申请号：US11605678
申请日：2006-11-29
IPC分类号： F01D25/00
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/712
摘要： A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.
摘要翻译： 燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。 每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的凹槽相关联。 凹口袋及其相关的刀刃密封件产生一对涡流，防止泄漏到涡轮部分的径向内部。
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公开(公告)号：US10119468B2
公开(公告)日：2018-11-06
申请号：US13366597
申请日：2012-02-06
摘要： A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.
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公开(公告)号：US09528391B2
公开(公告)日：2016-12-27
申请号：US13551149
申请日：2012-07-17
CPC分类号： F01D25/243 , F01D25/12 , F02C6/08 , F04D29/522 , F05D2240/12 , F05D2260/606 , Y02T50/671
摘要： An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The opening extends through the arcuate case wall. The boss extends radially from the outer surface of arcuate case wall and surrounds the opening. The contouring surrounds the opening along the inner surface of the arcuate case wall within the boss.
摘要翻译： 用于燃气涡轮发动机的轴向延伸的外壳包括弧形壳体壁，开口，凸台和轮廓。 弧形外壳壁具有内表面和外表面。 开口延伸穿过弧形外壳壁。 凸台从弧形外壳壁的外表面径向延伸并围绕开口。 轮廓沿着凸起部内的弓形壳体壁的内表面围绕开口。
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公开(公告)号：US20140023487A1
公开(公告)日：2014-01-23
申请号：US13551149
申请日：2012-07-17
CPC分类号： F01D25/243 , F01D25/12 , F02C6/08 , F04D29/522 , F05D2240/12 , F05D2260/606 , Y02T50/671
摘要： An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The opening extends through the arcuate case wall. The boss extends radially from the outer surface of arcuate case wall and surrounds the opening. The contouring surrounds the opening along the inner surface of the arcuate case wall within the boss.
摘要翻译： 用于燃气涡轮发动机的轴向延伸的外壳包括弧形壳体壁，开口，凸台和轮廓。 弧形外壳壁具有内表面和外表面。 开口延伸穿过弧形外壳壁。 凸台从弧形外壳壁的外表面径向延伸并围绕开口。 轮廓沿着凸起部内的弓形壳体壁的内表面围绕开口。
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公开(公告)号：US20130199205A1
公开(公告)日：2013-08-08
申请号：US13366597
申请日：2012-02-06
IPC分类号： F02C6/08
CPC分类号： F02C6/08 , F01D9/023 , F01D9/065 , F02C7/185 , F02C9/18 , F05D2260/601 , F05D2270/17 , F05D2270/301 , Y02T50/675
摘要： A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.
摘要翻译： 一种用于燃气涡轮发动机的放气系统，包括具有入口端并延伸到出口端的管道。 管道的入口端设置有中心插入件。 在另一个特征中，可以存在多个管道，并且多个管道的入口端部至少间隔开90°。 在另一个特征中，压缩机可以具有扩散器，其具有在内护罩的下游端的上游的护罩，其具有外护罩，其终止于在内护罩的下游端的上游的位置， 管道。
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公开(公告)号：US20100303610A1
公开(公告)日：2010-12-02
申请号：US12474822
申请日：2009-05-29
摘要： A stator assembly for a gas turbine engine is provided having an annular body, an inner gas path platform, a plurality of fairings, and at least one nozzle. The annular body has an outer gas path platform and a circumferentially extending annular cavity disposed radially outside of the outer gas path platform. The fairings extend radially between the inner gas path platform and the outer gas path platform. Each fairing includes a gas passage extending from the annular cavity through the inner gas path platform. The at least one nozzle has an inlet orifice disposed outside of the annular cavity and an exit orifice disposed within the annular cavity. The exit orifice is oriented within the annular cavity such that cooling air exiting the nozzle travels in a substantially circumferential direction within the annular cavity.
摘要翻译： 提供了一种用于燃气涡轮发动机的定子组件，其具有环形体，内部气体路径平台，多个整流罩和至少一个喷嘴。 环形体具有外部气体通道平台和设置在外部气体通道平台的径向外侧的周向延伸的环形空腔。 整流罩在内部气体通道平台和外部气体通道平台之间径向延伸。 每个整流罩包括从环形空腔穿过内部气体通道平台延伸的气体通道。 至少一个喷嘴具有设置在环形空腔外部的入口孔和设置在环形空腔内的出口孔。 出口孔定向在环形空腔内，使得离开喷嘴的冷却空气在环形空腔内沿大致圆周方向行进。
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