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1. 发明授权

EP1923539B1 Gas turbine with active tip clearance control 有权
标题翻译：燃气轮机用活性叶片尖端间隙控制
公开(公告)号：EP1923539B1
公开(公告)日：2016-11-02
申请号：EP07120717.9
申请日：2007-11-14
申请人： GENERAL ELECTRIC COMPANY
发明人： Seitzer, Kenneth Edward , Sak, Wojciech , Dong, Zhifeng , Ziegler, Robert Paul , Glynn, Christopher Charles
IPC分类号： F01D11/24
CPC分类号： F01D11/24 , Y02T50/672

2. 发明授权

EP1686243B1 Turbine engine stator including shape memory alloy and blade clearance control 有权
标题翻译：涡轮定子形状记忆合金和叶片游戏控制
公开(公告)号：EP1686243B1
公开(公告)日：2016-09-07
申请号：EP06250412.1
申请日：2006-01-25
申请人： GENERAL ELECTRIC COMPANY
发明人： Albers, Robert Joseph , Ruiz, Rafael , Boyle, Marcia , Glynn, Christopher Charles
IPC分类号： F01D11/24 , F01D11/18
CPC分类号： F01D11/18 , F01D11/24 , F05D2300/505

3. 发明公开

EP1686243A3 Turbine engine stator including shape memory alloy and blade clearance control 有权
标题翻译：涡轮定子形状记忆合金和叶片游戏控制
公开(公告)号：EP1686243A3
公开(公告)日：2012-05-16
申请号：EP06250412.1
申请日：2006-01-25
申请人： GENERAL ELECTRIC COMPANY
发明人： Albers, Robert Joseph , Ruiz, Rafael , Boyle, Marcia , Glynn, Christopher Charles
IPC分类号： F01D11/24 , F01D11/18
CPC分类号： F01D11/18 , F01D11/24 , F05D2300/505
摘要： A turbine engine stator assembly (18) in juxtaposition across a radial gap (26) with a rotary blading assembly (11) includes a radially movable shroud (20) and a gap control member (28) made of at least one shape memory alloy (SMA). The SMA is selected and preconditioned to deform pre-selected amounts to change the radial length of the gap (26) during engine operation responsive to temperature about the SMA. A fluid flow means (30) delivers fluid (34) to the SMA at pre-selected temperatures during engine operation.

4. 发明公开

EP2336026A2 Integrated Nacelle Assembly 有权
标题翻译： Integrierte Gondelbaugruppe
公开(公告)号：EP2336026A2
公开(公告)日：2011-06-22
申请号：EP10195753.8
申请日：2010-12-17
申请人： General Electric Company
发明人： Lachapelle, Donald George , Glynn, Christopher Charles , Gardner, Donald Lee , Mitchell, Stephen Craig , Srinivas, Mullahalli Venkataramaniah , Rainous, Edward Atwood , Pennekamp, David Lance
IPC分类号： B64D27/26 , B64D27/18
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/264 , B64D2027/266 , B64D2027/268
摘要： An assembly includes a unitary nacelle structure (11) and an integrated fan housing (30) for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl (50) region, and is configured to at least partially circumscribe the integrated fan housing (30). The integrated fan housing (30) comprises an integral composite structure and includes a fan case (32) sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes (38). The unitary nacelle structure (11) cooperates with the integrated fan housing (30) to transfer static and dynamic loads directly to a support structure (22), rather than through the engine core, to minimize backbone bending.
摘要翻译：组件包括用于燃气涡轮发动机组件的整体式机舱结构（11）和一体式风扇壳体（30）。整体式机舱结构包括入口区域和风扇整流罩（50）区域，并且构造成至少部分地围绕集成风扇壳体（30）。集成风扇壳体（30）包括整体复合结构，并且包括风扇壳体（32），其尺寸和构造用于环绕相关联的燃气涡轮发动机的风扇叶片组件，风扇轮毂和多个风扇出口导叶（38 ）。整体式机舱结构（11）与集成风扇壳体（30）配合，以将静态和动态负载直接传递到支撑结构（22），而不是通过发动机芯，以最小化主干弯曲。

5. 发明授权

EP1191191B1 Bearing assembly for a gas turbine engine 有权
标题翻译： LageranordnungfürGasturbinentriebwerk
公开(公告)号：EP1191191B1
公开(公告)日：2010-03-10
申请号：EP01307838.1
申请日：2001-09-14
申请人： GENERAL ELECTRIC COMPANY
发明人： Allmon, Barry Lynn , Glynn, Christopher Charles , Fisher, Kenneth Lee , Mollmann, Daniel Edward , Corattiyil, Bala , Vondrell, Randy Marinus , Schilling, Jan Christopher , Penn, Morris Green , Gambone, Michael Joseph
IPC分类号： F01D21/04
CPC分类号： F01D25/16 , F01D21/045 , F05B2260/3011 , F16C19/06 , F16C19/26 , F16C23/084 , F16C33/60 , F16C2360/23 , Y02T50/671 , Y10S416/50

6. 发明公开

EP1852573A2 Sealing assembly for gas turbine engines 审中-公开
标题翻译： DichtungsanordnungfürGasturbinen
公开(公告)号：EP1852573A2
公开(公告)日：2007-11-07
申请号：EP07107277.1
申请日：2007-05-01
申请人： The General Electric Company
发明人： Glynn, Christopher Charles , Herron, William Lee , Albers, Joseph C.
IPC分类号： F01D11/04 , F01D25/18 , F16J15/16
CPC分类号： F01D11/04 , F01D25/183
摘要： A seal assembly (100) for a gas turbine engine (10) including a stationary stator member (102) and a rotating member (104). The seal assembly includes a primary seal assembly (106), and a secondary seal assembly (108), the primary seal assembly including a moveable stator member (110) including at least one keyed slot (118), and at least one biasing member (114) including at least one key (116) slidably coupled within the at least one keyed slot to facilitate aligning the primary seal assembly and the secondary seal assembly with respect to the gas turbine engine.
摘要翻译：一种用于燃气涡轮发动机（10）的密封组件（100），包括固定定子构件（102）和旋转构件（104）。密封组件包括主密封组件（106）和次级密封组件（108），主密封组件包括可移动的定子构件（110），其包括至少一个键槽（118）和至少一个偏置构件 114）包括可滑动地联接在所述至少一个键槽中的至少一个键（116），以便于相对于所述燃气涡轮发动机对准所述主密封组件和所述次密封组件。

7. 发明公开

EP1260673A2 Turbine cooling circuit 有权
标题翻译： Turbinenkühlung
公开(公告)号：EP1260673A2
公开(公告)日：2002-11-27
申请号：EP02251930.0
申请日：2002-03-19
申请人： GENERAL ELECTRIC COMPANY
发明人： Glynn, Christopher Charles , Wallace, Thomas Tracy , Dickman, Ronald Arthur , Shelton, Monty Lee
IPC分类号： F01D5/08 , F02C7/12
CPC分类号： F02C7/12 , F01D5/081 , F01D5/18 , Y02T50/673 , Y02T50/676
摘要： A turbine cooling circuit (32) includes a flow sleeve (34) having an aft end (36) for adjoining the rim (30a) of a turbine disk (30). A seal rotor (38, 42) is spaced from the aft end adjacent a row of inlet holes (40). An inducer (46) has an outlet (50) disposed radially outwardly from the sleeve inlet holes. And, a seal stator (52,54) surrounds the seal rotor to define a rotary seal disposed radially inwardly from the inducer outlet.
摘要翻译：涡轮机冷却回路（32）包括具有用于邻接涡轮盘（30）的轮辋（30a）的后端（36）的流动套筒（34）。密封转子（38,42）与邻近一排入口孔（40）的后端部间隔开。导流器（46）具有从套筒入口孔径向向外设置的出口（50）。并且，密封定子（52,54）围绕密封转子以限定从诱导器出口径向向内设置的旋转密封件。

8. 发明公开

EP0601864A1 Turbine frame 失效
标题翻译： Turbinenrahmen。
公开(公告)号：EP0601864A1
公开(公告)日：1994-06-15
申请号：EP93309926.9
申请日：1993-12-09
申请人： GENERAL ELECTRIC COMPANY
发明人： Czachor, Robert Paul , Glynn, Christopher Charles
IPC分类号： F01D25/16 , F01D9/06
CPC分类号： F01D9/065 , F01D25/162
摘要： A turbine frame 32 includes first and second coaxially disposed rings 36, 38 having a plurality of circumferentially spaced apart struts 40 extending therebetween. A plurality of clevises 52 join respective first ends 40a of the struts 40 to the first ring 36 for removably joining the struts 40 thereto. Each of the clevises 52 includes a base 54 removably fixedly joined to the first ring 36, and a pair of legs 62, 64 extending away from the base 54 and spaced apart to define a U-shaped clevis slot 66 receiving the strut first end 40a. The strut first end 40a is removably fixedly joined to the clevis legs 62, 64 by a pair of expansion bolts 70. The clevis base 54 includes a central aperture 60 aligned with a first port 48 in the first ring 36 for providing access therethrough. And, the strut first end 40a abuts the first ring 36 for carrying compressive loads therebetween and providing a seal therewith.
摘要翻译：涡轮机架32包括第一和第二同轴设置的环36,38，其具有在其间延伸的多个周向间隔开的支柱40。多个U形夹52将支柱40的相应的第一端40a连接到第一环36，以将支柱40可拆卸地连接到其上。每个夹头52包括可移除地固定地连接到第一环36的基座54和远离基座54延伸并间隔开的一对支脚62,64，以限定接纳支柱第一端40a的U形U形夹插槽66 。支柱第一端40a通过一对膨胀螺栓70可拆卸地固定地连接到U形夹腿62,64。U形夹座54包括与第一环36中的第一端口48对准的中心孔60，用于提供通过其中的通路。并且，支柱第一端40a抵靠第一环36，以承载它们之间的压缩载荷并与其一起提供密封。

9. 发明公开

EP2336026A3 Integrated Nacelle Assembly 有权
标题翻译：集成的机舱组件
公开(公告)号：EP2336026A3
公开(公告)日：2017-05-24
申请号：EP10195753.8
申请日：2010-12-17
申请人： General Electric Company
发明人： Lachapelle, Donald George , Glynn, Christopher Charles , Gardner, Donald Lee , Mitchell, Stephen Craig , Srinivas, Mullahalli Venkataramaniah , Rainous, Edward Atwood , Pennekamp, David Lance
IPC分类号： B64D27/26 , B64D27/18
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/264 , B64D2027/266 , B64D2027/268
摘要： An assembly includes a unitary nacelle structure (11) and an integrated fan housing (30) for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl (50) region, and is configured to at least partially circumscribe the integrated fan housing (30). The integrated fan housing (30) comprises an integral composite structure and includes a fan case (32) sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes (38). The unitary nacelle structure (11) cooperates with the integrated fan housing (30) to transfer static and dynamic loads directly to a support structure (22), rather than through the engine core, to minimize backbone bending.
摘要翻译：一种组件包括用于燃气涡轮发动机组件的整体式机舱结构（11）和整体式风扇壳体（30）。整体式机舱结构包括入口区域和风扇罩（50）区域，并且构造成至少部分地包围整体式风扇壳体（30）。集成风扇壳体（30）包括整体复合结构并且包括风扇壳体（32），该风扇壳体的尺寸和构造被设计成用于环绕相关联的燃气涡轮发动机的风扇叶片组件，风扇轮毂和多个风扇出口导叶（38 ）。整体式机舱结构（11）与集成式风扇壳体（30）协作以将静态和动态负载直接传递到支撑结构（22），而不是通过发动机芯，以使主干弯曲最小化。

10. 发明授权

EP1431664B1 MOUNTING ASSEMBLY FOR THE AFT END OF A CERAMIC MATRIX COMPOSITE LINER IN A GAS TURBINE ENGINE COMBUSTOR 有权
标题翻译： ASSEMBLY燃烧室的燃气轮机的陶瓷基复合材料的壁的后边缘的
公开(公告)号：EP1431664B1
公开(公告)日：2011-10-05
申请号：EP03256559.0
申请日：2003-10-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Mitchell, Krista Anne , Noe, Mark Eugene , Wells, Thomas Allen , Bulman, David Edward , Hansel, Harold Ray , Glynn, Christopher Charles , Bibler, John David , Charneski, Joseph John , Darkins, Jr., Toby George , Burns, Craig Patrick
IPC分类号： F23R3/60
CPC分类号： F23R3/60 , F05B2230/606 , F23R3/007

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