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1. 发明授权

US5470198A Sealing structures for gas turbine engines 失效
标题翻译：燃气轮机发动机密封结构
公开(公告)号：US5470198A
公开(公告)日：1995-11-28
申请号：US299061
申请日：1994-08-31
申请人： Ian W. R. Harrogate , David H. Taylor , Arthur B. Griffin , David W. Tuson
发明人： Ian W. R. Harrogate , David H. Taylor , Arthur B. Griffin , David W. Tuson
IPC分类号： F01D9/02 , F01D9/04 , F01D11/00 , F02C7/00 , F02C7/28 , F01D5/18
CPC分类号： F01D9/023 , F01D11/005 , Y02T50/671 , Y02T50/675
摘要： A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly extending between nozzle guide vanes and combustion chamber discharge nozzles. The nozzle guide vanes have platforms having extensions which in one embodiment overlap the downstream ends of the discharge nozzles. Cooling air is supplied to the upstream edge portions of the platforms through holes in flanges on the discharge nozzles. The seal assembly defines a chamber adjacent the platform extensions which is supplied with cooling air through metering holes in the seal assembly which provides part of a boundary for a cooling air chamber, the boundary of the chamber having cooling air holes for metering cooling air into the chamber to cool the upstream portion of the nozzle guide vane outer platforms. Cooling air exits the chamber through holes in the platform extensions to film cool them.
摘要翻译：燃气涡轮发动机中的冷却和密封装置包括在喷嘴导向叶片和燃烧室排出喷嘴之间延伸的密封组件。喷嘴导叶具有具有延伸部的平台，在一个实施例中，该延伸部与排放喷嘴的下游端重叠。冷却空气通过排放喷嘴上的凸缘中的孔被供应到平台的上游边缘部分。密封组件限定了邻近平台延伸部分的室，该冷却空气通过密封组件中的计量孔供应冷却空气，该冷却空气为冷却空气室提供了一部分边界，该室的边界具有冷却空气孔，用于将冷却空气计入以冷却喷嘴导向叶片外平台的上游部分。冷却空气通过平台延伸部分中的孔离开室以使其冷却。

2. 发明授权

US5407319A Sealing structures for gas turbine engines 失效
标题翻译：燃气轮机发动机密封结构
公开(公告)号：US5407319A
公开(公告)日：1995-04-18
申请号：US207626
申请日：1994-03-09
申请人： Ian W. R. Harrogate , David H. Taylor , Arthur B. Griffin , David W. Tuson
发明人： Ian W. R. Harrogate , David H. Taylor , Arthur B. Griffin , David W. Tuson
IPC分类号： F01D9/02 , F01D9/04 , F01D11/00 , F02C7/00 , F02C7/28 , F01D5/18
CPC分类号： F01D9/023 , F01D11/005 , Y02T50/671 , Y02T50/675
摘要： A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly (42,30) extending between nozzle guide vanes (20) and combustion chamber discharge nozzles (22). The nozzle guide vanes (20) have platforms (34,36) having extensions (34A,36A) which in one embodiment overlap the downstream ends of the discharge nozzles (22). Cooling air is supplied to the upstream edge portions of the platforms through holes (26,28C) in flanges (24,28) on the discharge nozzles (22). The seal assembly (42,30) defines a chamber (58,70) adjacent the platform extensions which is supplied with cooling air through metering holes (56,68) in the seal assembly. Cooling air exits the chamber (58,70) through holes (34B,36B) in the platform extensions to film cool them.
摘要翻译：燃气涡轮发动机中的冷却和密封装置包括在喷嘴导向叶片（20）和燃烧室排出喷嘴（22）之间延伸的密封组件（42,30）。喷嘴导向叶片（20）具有在一个实施例中与排放喷嘴（22）的下游端重叠的延伸部（34A，36A）的平台（34,36）。冷却空气通过排放喷嘴（22）上的凸缘（24,28）中的孔（26,28C）供应到平台的上游边缘部分。密封组件（42,30）限定了邻近平台延伸部的腔室（58,70），其通过密封组件中的计量孔（56,68）供应冷却空气。冷却空气通过平台延伸部中的孔（34B，36B）离开室（58,70），以使其冷却。

3. 发明授权

US5398496A Gas turbine engines 失效
标题翻译：燃气涡轮发动机
公开(公告)号：US5398496A
公开(公告)日：1995-03-21
申请号：US207614
申请日：1994-03-09
申请人： David H. Taylor , Arthur B. Griffin , David W. Tuson
发明人： David H. Taylor , Arthur B. Griffin , David W. Tuson
IPC分类号： F01D9/02 , F01D9/04 , F02C7/00 , F02C7/28 , F23R3/60
CPC分类号： F01D9/023 , F23R3/60 , Y02T50/675
摘要： A gas turbine engine component support assembly (30) comprises a pair of ring members (64) and (74) defining a slot in which a cranked flange (28) extending from the inner surfaces of an array of combustion chamber discharge nozzles (22) is located. One part (28B) of the cranked flange has projections (28C) which engage with radial slots (76) formed in one of the ring members (74) to provide cross-key location of the discharge nozzles. The support assembly (30) is located adjacent the radially inner platform of an array of nozzle guide vanes (20), and also provides support and location for the vanes.
摘要翻译：一种燃气涡轮发动机部件支撑组件（30）包括一对限定一个狭槽的环形部件（64）和（74），其中从燃烧室排放喷嘴（22）阵列的内表面延伸的曲柄凸缘（28）位于。曲柄法兰的一部分（28B）具有与形成在一个环形构件（74）中的径向槽（76）接合的突起（28C），以提供排出喷嘴的交叉键位置。支撑组件（30）位于喷嘴导向叶片（20）阵列的径向内部平台附近，并且还为叶片提供支撑和定位。

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