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1. 发明申请

US20050072163A1 MOUNTING ASSEMBLY FOR IGNITER IN A GAS TURBINE ENGINE COMBUSTOR HAVING A CERAMIC MATRIX COMPOSITE LINER 失效
标题翻译：在具有陶瓷基体复合材料的气体涡轮发动机燃烧器中的IGNITER安装组件
公开(公告)号：US20050072163A1
公开(公告)日：2005-04-07
申请号：US10341850
申请日：2003-01-14
申请人： Thomas Wells , David Bulman , Mark Noe , Harold Hansel , Christopher Glynn
发明人： Thomas Wells , David Bulman , Mark Noe , Harold Hansel , Christopher Glynn
IPC分类号： F02C7/264 , F16F3/04 , F23R3/60
CPC分类号： F16F3/04 , F02C7/264 , F23D2207/00 , F23D2211/00 , F23R3/60 , F23R2900/00012
摘要： An assembly for mounting an igniter in a gas turbine engine combustor between an outer casing and an outer liner, wherein a longitudinal centerline axis extends through the gas turbine engine. The igniter mounting assembly includes a first spring member encircling a portion of said igniter and being positioned between a surface adjacent the outer casing and an outer surface of the outer liner, a first ring member connected to a first end of the first spring member adjacent the outer surface of the outer liner, and a second ring member connected to a second end of the first spring member adjacent the surface adjacent the outer casing. Accordingly, the igniter is able to maintain substantial alignment with respect to an opening in the outer liner while moving radially and/or axially with respect to the outer liner as the outer casing experiences thermal growth greater than the outer liner.
摘要翻译：一种用于将点火器安装在外壳和外衬套之间的燃气涡轮发动机燃烧器中的组件，其中纵向中心线轴线延伸穿过燃气涡轮发动机。点火器安装组件包括围绕所述点火器的一部分并且位于邻近外壳的表面和外衬套的外表面之间的第一弹簧构件，与第一弹簧构件的第一端相邻的第一环构件，外衬套的外表面和与邻近外壳的表面相邻的第一弹簧构件的第二端连接的第二环构件。因此，随着外套经历大于外衬套的热生长，点火器能够相对于外衬套的开口保持基本对准，同时相对于外衬套径向和/或轴向移动。

2. 发明申请

US20070140843A1 Methods and apparatus for assembling gas turbine engine stator assemblies 有权
标题翻译：燃气轮机发动机定子总成的组装方法和装置
公开(公告)号：US20070140843A1
公开(公告)日：2007-06-21
申请号：US11303884
申请日：2005-12-16
申请人： Vincent Drerup , Harold Hansel , Ching-Pang Lee
发明人： Vincent Drerup , Harold Hansel , Ching-Pang Lee
IPC分类号： F04D29/54
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 is provided. The method comprises coupling a first turbine nozzle 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 including a substantially planar body. The method also comprises forming at least one catch 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 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的方法。该方法包括将第一涡轮喷嘴联接在发动机内，将第二涡轮喷嘴与第一涡轮喷嘴周向相邻地连接，使得在第一涡轮喷嘴和第二涡轮喷嘴之间限定间隙，并提供包括基本上平面的主体的至少一个花键密封。该方法还包括形成至少一个止动件以从至少一个花键密封件的本体部分向外延伸，以及将至少一个花键密封件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中，以便减少泄漏通过所述间隙，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。

3. 发明申请

US20070104571A1 Methods and apparatus for assembling turbine engines 失效
标题翻译：涡轮发动机组装方法及装置
公开(公告)号：US20070104571A1
公开(公告)日：2007-05-10
申请号：US11271101
申请日：2005-11-10
申请人： Vincent Drerup , Harold Hansel , James Ketzer , Ching-Pang Lee
发明人： Vincent Drerup , Harold Hansel , James Ketzer , Ching-Pang Lee
IPC分类号： F01D9/00
CPC分类号： F02C7/28 , F01D11/005 , F05D2240/12 , F05D2260/30 , Y10T29/49297 , Y10T29/4932 , Y10T29/49323
摘要： A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle 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 including a substantially planar body. The method also comprises forming at least one retainer tab 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 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：提供一种用于组装燃气涡轮发动机的方法。该方法包括将第一涡轮喷嘴联接在发动机内，将第二涡轮喷嘴与第一涡轮喷嘴周向相邻地连接，使得在第一涡轮喷嘴和第二涡轮喷嘴之间限定间隙，并提供包括基本上平面的主体的至少一个花键密封。该方法还包括形成至少一个保持器突片以从至少一个花键密封件的主体部分向外延伸，以及将至少一个花键密封件插入限定在第一和第二涡轮喷嘴中的至少一个中的狭槽中，以便于减少通过所述间隙的泄漏，使得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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