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公开(公告)号：EP1785592B1
公开(公告)日：2013-09-25
申请号：EP06255762.4
申请日：2006-11-09
CPC分类号： F02C7/28 , F01D11/005 , F05D2240/12 , F05D2260/30 , Y10T29/49297 , Y10T29/4932 , Y10T29/49323
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公开(公告)号：EP1798380B1
公开(公告)日：2015-11-11
申请号：EP06126228.3
申请日：2006-12-15
IPC分类号： F01D11/00
CPC分类号： F01D9/041 , F01D11/005 , F05D2240/57 , F05D2260/30 , F05D2260/33 , Y02T50/673
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公开(公告)号：EP1798380A2
公开(公告)日：2007-06-20
申请号：EP06126228.3
申请日：2006-12-15
IPC分类号： F01D11/00
CPC分类号： F01D9/041 , F01D11/005 , F05D2240/57 , F05D2260/30 , F05D2260/33 , Y02T50/673
摘要： A method for assembling a gas turbine engine (10) is provided. The method comprises coupling a first turbine nozzle (50) within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal (100) including a substantially planar body (120). The method also comprises forming at least one catch (122) to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot (60) defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that a portion of the at least one spline seal is received within a recess defined within the turbine nozzle slot to facilitate retaining the at least one spline seal within the turbine nozzle slot.
摘要翻译： 提供一种用于组装燃气涡轮发动机（10）的方法。 该方法包括联接发动机内的第一涡轮喷嘴（50），将第二涡轮喷嘴与第一涡轮喷嘴周向相邻地连接，使得在第一和第二涡轮喷嘴之间限定间隙，并提供至少一个花键密封（100），其包括 基本平坦的主体（120）。 该方法还包括形成至少一个止动件（122），以从所述至少一个花键密封件的主体部分向外延伸，并将所述至少一个花键密封件插入定义在第一和第 第二涡轮喷嘴以便于减少通过所述间隙的泄漏，使得所述至少一个花键密封件的一部分被容纳在限定在所述涡轮喷嘴槽内的凹部内，以便于将所述至少一个花键密封件保持在所述涡轮喷嘴槽内。
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公开(公告)号：EP1798380A3
公开(公告)日：2014-06-11
申请号：EP06126228.3
申请日：2006-12-15
IPC分类号： F01D11/00
CPC分类号： F01D9/041 , F01D11/005 , F05D2240/57 , F05D2260/30 , F05D2260/33 , Y02T50/673
摘要： A method for assembling a gas turbine engine (10) is provided. The method comprises coupling a first turbine nozzle (50) within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal (100) including a substantially planar body (120). The method also comprises forming at least one catch (122) to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot (60) defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that a portion of the at least one spline seal is received within a recess defined within the turbine nozzle slot to facilitate retaining the at least one spline seal within the turbine nozzle slot.
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公开(公告)号：EP1785592A3
公开(公告)日：2012-08-01
申请号：EP06255762.4
申请日：2006-11-09
CPC分类号： F02C7/28 , F01D11/005 , F05D2240/12 , F05D2260/30 , Y10T29/49297 , Y10T29/4932 , Y10T29/49323
摘要： A sealing assembly (50) for gas turbine engine (10) is provided.
At least a spline seal (100), a substantially planar body covers the gap defined between a first turbine nozzle (50) within the engine and a second turbine nozzle circumferentially adjacent the first turbine nozzle. It comprises at least one retainer tab (122) extending outward from the body portion of the at least one spline seal, and is inserted into a slot (222) defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that the at least one retainer tab facilitates retaining the retainer tab within the turbine nozzle slot.-
公开(公告)号：EP1785592A2
公开(公告)日：2007-05-16
申请号：EP06255762.4
申请日：2006-11-09
IPC分类号： F01D11/00
CPC分类号： F02C7/28 , F01D11/005 , F05D2240/12 , F05D2260/30 , Y10T29/49297 , Y10T29/4932 , Y10T29/49323
摘要： A sealing assembly (50) for gas turbine engine (10) is provided.
At least a spline seal (100), a substantially planar body covers the gap defined between a first turbine nozzle (50) within the engine and a second turbine nozzle circumferentially adjacent the first turbine nozzle. It comprises at least one retainer tab (122) extending outward from the body portion of the at least one spline seal, and is inserted into a slot (222) defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that the at least one retainer tab facilitates retaining the retainer tab within the turbine nozzle slot.摘要翻译： 提供了一种用于燃气涡轮发动机（10）的密封组件（50）。 至少一个花键密封件（100），基本平坦的主体覆盖限定在发动机内的第一涡轮喷嘴（50）和与第一涡轮喷嘴周向相邻的第二涡轮喷嘴之间的间隙。 它包括从至少一个花键密封件的主体部分向外延伸的至少一个保持片（122），并且插入到限定在第一和第二涡轮喷嘴中的至少一个中的狭槽（222）中，以便于减少通过 所述间隙使得所述至少一个保持器突片有助于将保持器突片保持在涡轮喷嘴槽内。
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公开(公告)号：EP0542403A1
公开(公告)日：1993-05-19
申请号：EP92306006.5
申请日：1992-06-30
CPC分类号： F01D9/042 , F01D5/187 , F01D9/065 , F01D11/005 , F05D2260/60
摘要： An air transfer assembly for a gas turbine engine is provided. The assembly transfers temperature control air (21) from an annular plenum (20) to an annular manifold (22) through an air transfer tube (15) interposed therebetween. The air transfer tube (15) prevents temperature control air leakage even though it is permitted to slide between limits set by an air transfer bushing assembly (10) and a manifold cup (30) formed in the annular manifold (22). The air transfer bushing (10) is removable and is installed in an aperature in an outer support. The manifold cup (30) is formed in the annular manifold.
摘要翻译： 提供了一种用于燃气涡轮发动机的空气传送组件。 组件通过插入其间的空气传输管（15）将温度控制空气（21）从环形增压室（20）传递到环形歧管（22）。 空气传输管（15）即使允许其在由空气传输衬套组件（10）和形成在环形歧管（22）中的歧管杯（30）设定的极限之间滑动，也防止温度控制空气泄漏。 空气传送衬套（10）是可移除的并且安装在外部支撑件的温度中。 歧管杯（30）形成在环形歧管中。
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