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31. 发明授权

EP1365154B1 Counterrotatable booster compressor assembly for a gas turbine engine 有权
标题翻译：防止旋转的增压压缩机用于燃气涡轮发动机
公开(公告)号：EP1365154B1
公开(公告)日：2007-05-02
申请号：EP03253260.8
申请日：2003-05-23
申请人： GENERAL ELECTRIC COMPANY
发明人： Prentice, Ian Francis , Busbey, Bruce Clark , Bond, Donald Ray , Crall, David William , Glynn, Christopher Charles
IPC分类号： F04D19/02 , F04D25/04 , F02C3/073 , F02C3/067
CPC分类号： F01D5/022 , F02C3/067 , F02K3/072 , F04D19/024 , F04D25/04

32. 发明授权

EP1008726B1 Fan decoupler system for a gas turbine engine 有权
标题翻译：一种用于鼓风机不耦合系统
公开(公告)号：EP1008726B1
公开(公告)日：2006-04-26
申请号：EP99309889.6
申请日：1999-12-09
申请人： GENERAL ELECTRIC COMPANY
发明人： Tseng, Wu-Yang , Glynn, Christopher Charles , Vondrell, Randy Marinus
IPC分类号： F01D21/04 , F01D25/16
CPC分类号： F01D21/045 , F01D21/04 , F01D25/16 , F01D25/162 , F05B2260/3011

33. 发明公开

EP1439350A2 Support assembly for a gas turbine engine combustor 审中-公开
标题翻译： Trägeranordnungfüreine Gasturbinenbrennkammer
公开(公告)号：EP1439350A2
公开(公告)日：2004-07-21
申请号：EP03257117.6
申请日：2003-11-12
申请人： GENERAL ELECTRIC COMPANY
发明人： Mitchell, Krista Anne , Noe, Mark Eugene , Glynn, Christopher Charles , Bulman, David Edward , Hansel, Harold Ray
IPC分类号： F23R3/60 , F23R3/00 , F23R3/50
CPC分类号： F23R3/007 , F05B2230/606 , F23R3/50 , F23R3/60 , F23R2900/00014
摘要： A support assembly for a gas turbine engine combustor (10) including an inner liner (18) and an inner casing (31) spaced therefrom, wherein a longitudinal centerline axis (12) extends through the gas turbine engine. The support assembly includes an annular inner support cone (34) located adjacent an aft end of said inner liner (18), an annular nozzle support (33) connected to the inner support cone (34), and a plurality of support members (102) connected at a first end to a forward end (40) of the inner liner (18) and connected at a second end to the inner support cone (34).
摘要翻译：一种用于燃气涡轮发动机燃烧器（10）的支撑组件，其包括与其间隔开的内衬（18）和内壳（31），其中纵向中心线轴线（12）延伸穿过燃气涡轮发动机。支撑组件包括邻近所述内衬（18）的后端定位的环形内支撑锥体（34），连接到内支撑锥体（34）的环形喷嘴支撑件（33）和多个支撑构件（102））在第一端连接到内衬（18）的前端（40）并且在第二端处连接到内支撑锥体（34）。

34. 发明公开

EP1431664A2 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：EP1431664A2
公开(公告)日：2004-06-23
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, Toby George Jr. , Burns, Craig Patrick
IPC分类号： F23R3/60
CPC分类号： F23R3/60 , F05B2230/606 , F23R3/007
摘要： A mounting assembly (36) for an aft end (38) of a liner of a gas turbine engine combustor includes a support member (40). The mounting assembly (36) includes a pin member (46) extending through each one of a plurality of circumferentially spaced openings (42) in a portion of the support member (40) for the combustor and into a plurality of partial openings (44) formed in the aft end (38) of the liner, with each pin member (46) including a head portion (48) at one end thereof, and a device (50) positioned within each opening (42) in the support member (40) so as to retain the pin members (42) therein. The pin members (42) and the support member (40) are able to slide radially and/or axially with respect to the liner aft end (38) as the support member (40) experiences thermal growth greater than the liner.
摘要翻译：用于在燃气涡轮发动机燃烧器的衬里的后端（38）的安装组件（36）包括支撑构件（40）。的安装组件（36）包括通过在用于燃烧器并进入部分开口的多个支承构件（40）的一部分沿周向间隔开的开口（42）的多个每一个延伸的销件（46）（44）形成在所述衬垫的后端（38），每个销件（46）包括在其一端的头部（48），并且每个开口（42）内定位的装置（50）（在支撑构件40 ），以便保持所述销部件（42）在其中。销部件（42）和支承构件（40）能够相对于所述衬管后端（38），作为支承构件（40）经历的热增长比衬垫更大径向和/或轴向地滑动。

35. 发明公开

EP1008726A3 Fan decoupler system for a gas turbine engine 有权
标题翻译：一种用于鼓风机不耦合系统
公开(公告)号：EP1008726A3
公开(公告)日：2004-01-02
申请号：EP99309889.6
申请日：1999-12-09
申请人： GENERAL ELECTRIC COMPANY
发明人： Tseng, Wu-Yang , Glynn, Christopher Charles , Vondrell, Randy Marinus
IPC分类号： F01D21/04 , F01D25/16
CPC分类号： F01D21/045 , F01D21/04 , F01D25/16 , F01D25/162 , F05B2260/3011
摘要： A support structure (210) for a gas turbine engine (200) includes a support arm (212) extending between a low pressure shaft (202) and a plurality of rotor blades (236). The support arm (212) includes a fuse (220) having a low failure point. A high pressure stub shaft (270) axially and radially supports the low pressure shaft (202) after fuse failure. An axial gap A between a portion of the low pressure shaft (202) and the stub shaft (270) permits movement of the low pressure shaft (202) after fuse failure. A radial gap B between the stub shaft (270) and the low pressure shaft (202) allows radial deflection. of the low pressure rotor system after fuse failure.

36. 发明公开

EP1172523A3 Method and apparatus for supplying cooling air to turbine rotors 有权
标题翻译：提供方法和设备，用于涡轮转子冷却空气
公开(公告)号：EP1172523A3
公开(公告)日：2003-11-05
申请号：EP01304245.2
申请日：2001-05-11
申请人： GENERAL ELECTRIC COMPANY
发明人： Wallace, Thomas Tracy , Shelton, Monty Lee , Lenahan, Dean Thomas , Glynn, Christopher Charles , Clements, Jeffrey Donald , Kalb, Barry John
IPC分类号： F01D5/08
CPC分类号： F01D5/082 , F01D5/085 , F05D2240/12 , F05D2240/40 , F05D2250/71 , F05D2260/30
摘要： A gas turbine engine rotor assembly includes a plurality of aerodynamic devices (66) to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft (44) that includes a plurality of openings (52). The aerodynamic devices include a pair of vane segments (140) and a pair of sidewalls (142). A contoured outer surface (132) includes an opening (74) and permits the aerodynamic device to be positioned against an inner surface (50) of the rotor shaft, and a flange ring (60, 64) defines a pocket (65). The aerodynamic device fits within the pocket to concentrically align the openings (52,74).

37. 发明公开

EP1191191A2 Turbine bearing 有权
标题翻译：用于燃气涡轮发动机的轴承布置
公开(公告)号：EP1191191A2
公开(公告)日：2002-03-27
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： F01D25/16
CPC分类号： F01D25/16 , F01D21/045 , F05B2260/3011 , F16C19/06 , F16C19/26 , F16C23/084 , F16C33/60 , F16C2360/23 , Y02T50/671 , Y10S416/50
摘要： A rotor assembly (40) for a gas turbine engine includes a bearing assembly (46) that reduces dynamic loads to a support frame (44) and static bending to the rotor assembly during periods of rotor imbalance. The rotor assembly includes a rotor shaft (42) coupled to a fan and supported longitudinally with a plurality of bearing assemblies on a support frame. A number two bearing assembly includes a paired race (50), a bearing (48), and a mounting race (102). The mounting race includes a spherical face and is secured to the bearing assembly with a retainer (104) that plastically fails at a pre-determined moment load.

38. 发明公开

EP1079069A2 Steam cooling system for a gas turbine 有权
标题翻译： Dampfkühlungssystemfüreine Gasturbine
公开(公告)号：EP1079069A2
公开(公告)日：2001-02-28
申请号：EP00304909.5
申请日：2000-06-09
申请人： GENERAL ELECTRIC COMPANY
发明人： Wilson, Ian David , Barb, Kevin Joseph , Li, Ming Cheng , Hyde, Susan Marie , Mashey, Thomas Charles , Wesorick, Ronald Richard , Glynn, Christopher Charles , Hemsworth, Martin C.
IPC分类号： F01D5/08 , F02C7/16
CPC分类号： F01D5/085 , F02C7/16 , F05D2260/2322 , Y02T50/676
摘要： The steam cooling circuit for a gas turbine includes a bore tube assembly (48) supplying steam to circumferentially spaced radial tubes (54) coupled to supply elbows (206) for transitioning the radial steam flow in an axial direction along steam supply tubes (56) adjacent the rim of the rotor. The supply tubes supply steam to circumferentially spaced manifold segments (120) located on the aft side of the 1-2 spacer for supplying steam to the buckets (22, 24) of the first and second stages. Spent return steam from these buckets flows to a plurality of circumferentially spaced return manifold segments disposed on the forward face of the 1-2 spacer. Crossover tubes (146) couple the steam supply from the steam supply manifold segments through the 1-2 spacer to the buckets (22) of the first stage. Crossover tubes (196) through the 1-2 spacer also return steam from the buckets of the second stage to the return manifold segments. Axially extending return tubes (58) convey spent cooling steam from the return manifold segments to radial tubes (80) via return elbows (216).
摘要翻译：用于燃气涡轮机的蒸汽冷却回路包括孔管组件（48），用于将蒸汽供应到与供应弯头（206）相连的周向间隔开的径向管（54），用于沿着沿着蒸汽供应管（56）的轴向转换径向蒸汽流，邻近转子的边缘。供应管向位于1-2间隔件的后侧的周向隔开的歧管段（120）供应蒸汽，以将蒸汽供应到第一和第二级的桶（22,24）。来自这些铲斗的废水返回蒸汽流向设置在1-2间隔物的前表面上的多个周向间隔开的返回歧管段。交叉管（146）将来自蒸汽供应歧管段的蒸汽供应通过1-2间隔件耦合到第一级的桶（22）。通过1-2间隔物的交叉管（196）还将蒸汽从第二级的桶返回到回流歧管段。轴向延伸的返回管（58）通过返回弯头（216）将废冷却蒸汽从返回歧管段传送到径向管（80）。

39. 发明授权

EP0601864B1 Turbine frame 失效
标题翻译： Turbinenrahmen
公开(公告)号：EP0601864B1
公开(公告)日：1997-07-30
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

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