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1. 发明授权

EP1586744B1 Variable vane assembly for a gas turbine engine 有权
标题翻译：一个燃气涡轮机的可变叶片组件
公开(公告)号：EP1586744B1
公开(公告)日：2010-12-22
申请号：EP05252319.8
申请日：2005-04-14
申请人： GENERAL ELECTRIC COMPANY
发明人： Cormier, Nathan Gerard , Bowen, Wayne Ray , Rhoda, James Edwin , Headley, Mitchell Jay
IPC分类号： F01D17/16 , F01D9/04
CPC分类号： F04D29/563 , F01D17/162 , Y10T403/587

2. 发明授权

EP1209320B1 Fan disk configuration 有权
标题翻译：疤痕磁盘配置用于风扇转子
公开(公告)号：EP1209320B1
公开(公告)日：2006-06-28
申请号：EP01309912.2
申请日：2001-11-26
申请人： GENERAL ELECTRIC COMPANY
发明人： Forrester, James Michael , Bolt, Janine Elizabeth , Rhoda, James Edwin , Stevenson, Joseph Timothy
IPC分类号： F01D5/02 , F01D21/04 , F01D5/30
CPC分类号： F01D5/326 , F01D5/06 , F01D11/008 , F01D21/045 , F05D2250/141 , Y02T50/671 , Y02T50/673

3. 发明公开

EP0731184A1 Laser shock peened gas turbine engine compressor airfoil edges 失效
标题翻译： Gasturbinenschaufeln mit Laserschock behandelte Kanten
公开(公告)号：EP0731184A1
公开(公告)日：1996-09-11
申请号：EP96301458.4
申请日：1996-03-05
申请人： GENERAL ELECTRIC COMPANY
发明人： Mannava, Seetharamaiah , Jacobs, Larry George , Rhoda, James Edwin , Rainous, Edward Atwood , Halila, Herbert
IPC分类号： C21D10/00 , F01D5/28
CPC分类号： B23P6/002 , C21D10/005 , F01D5/286 , Y02T50/671 , Y02T50/673
摘要： Gas turbine engine compressor component that has an airfoil such as a compressor blade with a metallic airfoil having a leading edge and a trailing edge and at least one laser shock peened surface extending radially along at least a portion of the leading edge and a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.
摘要翻译：具有翼型的燃气涡轮发动机压缩机部件，例如具有前缘和后缘的金属翼型的压缩机叶片，以及沿着前缘的至少一部分径向延伸的至少一个激光冲击喷丸表面和具有深度的区域通过激光冲击喷丸（LSP）延伸到激光冲击喷丸表面的翼型中施加的压缩残余应力。

4. 发明公开

EP1087100A3 Compressor rotor configuration 有权
标题翻译：压缩机转子配置
公开(公告)号：EP1087100A3
公开(公告)日：2004-01-02
申请号：EP00306179.3
申请日：2000-07-20
申请人： GENERAL ELECTRIC COMPANY
发明人： Mielke, Mark Joseph , Rhoda, James Edwin , Bulman, David Edward , Burns, Craig Patrick , Smith, Paul Michael , Suffoletta, Daniel Gerard , Ballman, Steven Mark , Zylka, Richard Patrick , Egan, Lawrence J.
IPC分类号： F01D5/02 , F01D5/14 , F04D29/32
CPC分类号： F01D5/143 , F01D5/02 , F01D5/06 , F04D29/321
摘要： A gas turbine engine rotor assembly including a rotor (12) having a radially outer rim (18) with an outer surface (204) shaped to reduce circumferential rim stress concentration between each blade (24) and the rim. Additionally, the shape of the outer surface directs air flow away from an interface between a blade and the rim to reduce aerodynamic performance losses between the rim and blades. In an exemplary embodiment, the outer surface of the rim has a concave shape (210) between adjacent blades with apexes located at interfaces between the blades and the rim.
摘要翻译：一种包括转子（12）的燃气涡轮发动机转子组件，所述转子具有径向外缘（18），所述径向外缘具有外表面（204），所述外表面成形为减小每个叶片（24）与所述边缘之间的周向边缘应力集中。此外，外表面的形状引导空气流离开叶片和轮辋之间的界面，以降低轮辋和叶片之间的空气动力学性能损失。在示例性实施例中，边沿的外表面在相邻叶片之间具有凹入形状（210），顶点位于叶片和边沿之间的交界处。

5. 发明公开

EP1045156A3 Bushing assembly with removable wear sleeve 有权
标题翻译：可拆卸比赛套筒组件
公开(公告)号：EP1045156A3
公开(公告)日：2001-08-22
申请号：EP00303124.2
申请日：2000-04-13
申请人： GENERAL ELECTRIC COMPANY
发明人： Bishop, Michael J. , Lammas, Andrew John , Rhoda, James Edwin
IPC分类号： F16C17/02 , F01D17/16 , F16C33/20
CPC分类号： F16C33/201 , F16C3/00 , F16C17/02
摘要： A bushing assembly (24) as a means to enable guided movement of a shaft (17) in an opening of a housing (18) comprises a stationary bushing support (26) carried by a housing internal wall (20). The bushing support (26) has a support internal wall (28) defining a bushing support opening (30) through the bushing support (26) to receive a movable shaft (17). Carried by the shaft (17) is a removable wear sleeve (32) having a wear sleeve outer wall (34) in juxtaposition with and spaced apart from the support internal wall (28) to permit relative axial movement of the wear sleeve (32) with the shaft (17) within the bushing support opening (30). Disposed between and for contact with the support internal wall (28) and with the wear sleeve outer wall (34) is an anti-friction layer (36).

6. 发明公开

EP1087100A2 Compressor rotor configuration 有权
标题翻译： Kompressorrotor- Konfiguration
公开(公告)号：EP1087100A2
公开(公告)日：2001-03-28
申请号：EP00306179.3
申请日：2000-07-20
申请人： GENERAL ELECTRIC COMPANY
发明人： Mielke, Mark Joseph , Rhoda, James Edwin , Bulman, David Edward , Burns, Craig Patrick , Smith, Paul Michael , Suffoletta, Daniel Gerard , Ballman, Steven Mark , Zylka, Richard Patrick , Egan, Lawrence J.
IPC分类号： F01D5/02 , F01D5/14 , F04D29/32
CPC分类号： F01D5/143 , F01D5/02 , F01D5/06 , F04D29/321
摘要： A gas turbine engine rotor assembly including a rotor (12) having a radially outer rim (18) with an outer surface (204) shaped to reduce circumferential rim stress concentration between each blade (24) and the rim. Additionally, the shape of the outer surface directs air flow away from an interface between a blade and the rim to reduce aerodynamic performance losses between the rim and blades. In an exemplary embodiment, the outer surface of the rim has a concave shape (210) between adjacent blades with apexes located at interfaces between the blades and the rim.
摘要翻译：一种燃气涡轮发动机转子组件，包括具有径向外边缘（18）的转子（12），所述转子具有外表面（204），所述外表面（204）成形为减小每个叶片（24）和所述边缘之间的圆周边缘应力集中。此外，外表面的形状引导空气流离开叶片和轮辋之间的界面，以减小边缘和叶片之间的空气动力学性能损失。在示例性实施例中，边缘的外表面在相邻刀片之间具有凹形（210），其顶点位于刀片和边缘之间的界面处。

7. 发明公开

EP2236773A2 Variable stator vane contoured button 审中-公开
标题翻译： Konturierter Knopf einer verstellbaren Leitschaufel
公开(公告)号：EP2236773A2
公开(公告)日：2010-10-06
申请号：EP10155311.3
申请日：2010-03-03
申请人： General Electric Company
发明人： Mielke, Mark Joseph , Breeze-Springfellow, Andrew , Clark, David Scott , Rhoda, James Edwin , Peters, Gary Robert
IPC分类号： F01D17/16 , F01D9/04
CPC分类号： F01D17/162 , F04D29/563 , F05D2240/80 , F05D2250/711
摘要： A variable stator vane (15) airfoil (31) is mounted on a button (54) centered about a rotational axis (20) and includes circular leading and trailing edges (52, 53) circumscribed about the rotational axis (20) at a button radius (R). Contoured pressure and suction sides (58, 59) extend from the circular leading edge (52) to the circular trailing edge (53) and are recessed inwardly from a perimeter (22) circumscribed about the rotational axis (20) at the button radius (R). One of upstream and downstream pressure side portions (24, 26) of the contoured pressure side (58) is straight and another of the upstream and downstream pressure side portions (24, 26) is curved. One of the upstream and downstream suction side portions (28, 30) is straight and another of the upstream and downstream suction side portions (28, 30) is curved. One of the upstream pressure side portion (24) and upstream suction side portion (28) is straight and another of the upstream pressure side portion (24) and upstream suction side portion (28) is curved.
摘要翻译：可变定子叶片（15）翼型件（31）安装在以旋转轴线（20）为中心的按钮（54）上，并且包括围绕旋转轴线（20）围绕的按钮的圆形前缘和后缘（52,53）半径（R）。轮廓压力和吸力侧面（58,59）从圆形前缘（52）延伸到圆形后缘（53），并且从围绕旋转轴线（20）的按钮半径（20）周边（22）向内凹陷 R）。成型压力侧（58）的上游侧压力侧部分（24）和下游侧压力侧部分（26）中的一个是直的，并且上游和下游压力侧部分（24,26）中的另一个是弯曲的。上游侧和下游侧吸入侧部分（28,30）中的一个是直的，并且上游和下游吸入侧部分（28,30）中的另一个是弯曲的。上游侧压力侧部24和上游吸入侧部28之一是直的，上游侧压力侧部24和上游吸入侧部28的另一方弯曲。

8. 发明公开

EP1586744A3 Variable vane assembly for a gas turbine engine 有权
标题翻译：一个燃气涡轮机的可变叶片组件
公开(公告)号：EP1586744A3
公开(公告)日：2008-04-23
申请号：EP05252319.8
申请日：2005-04-14
申请人： GENERAL ELECTRIC COMPANY
发明人： Cormier, Nathan Gerard , Bowen, Wayne Ray , Rhoda, James Edwin , Headley, Mitchell Jay
IPC分类号： F01D17/16 , F01D9/04
CPC分类号： F04D29/563 , F01D17/162 , Y10T403/587
摘要： A variable vane assembly (44) for a gas turbine engine includes a casing (50). The assembly comprises a variable vane (52) which includes a radially inner spindle (70) and a radially outer spindle (54). The radially inner and outer spindles are configured to rotatably couple the vane within the gas turbine engine. At least one of the radially inner and radially outer spindles comprises at least one groove (80) defined therein, at least one groove comprises at least one machined face (86), and a retainer for engaging the groove at least one machined face to securely couple the variable vane within the gas turbine engine, the retainer is configured to facilitate reducing wear of the variable vane.

9. 发明公开

EP1586744A2 Variable vane assembly for a gas turbine engine 有权
标题翻译： Verstellbare Leitschaufelanordnung einer Gurburbine
公开(公告)号：EP1586744A2
公开(公告)日：2005-10-19
申请号：EP05252319.8
申请日：2005-04-14
申请人： GENERAL ELECTRIC COMPANY
发明人： Cormier, Nathan Gerard , Bowen, Wayne Ray , Rhoda, James Edwin , Headley, Mitchell Jay
IPC分类号： F01D17/16 , F01D9/04
CPC分类号： F04D29/563 , F01D17/162 , Y10T403/587
摘要： A variable vane assembly (44) for a gas turbine engine includes a casing (50). The assembly comprises a variable vane (52) which includes a radially inner spindle (70) and a radially outer spindle (54). The radially inner and outer spindles are configured to rotatably couple the vane within the gas turbine engine. At least one of the radially inner and radially outer spindles comprises at least one groove (80) defined therein, at least one groove comprises at least one machined face (86), and a retainer for engaging the groove at least one machined face to securely couple the variable vane within the gas turbine engine, the retainer is configured to facilitate reducing wear of the variable vane.
摘要翻译：用于燃气涡轮发动机的可变叶片组件（44）包括壳体（50）。组件包括可变叶片（52），其包括径向内心轴（70）和径向外心轴（54）。径向内部和外部主轴构造成可旋转地联接燃气涡轮发动机内的叶片。径向内部和径向外部主轴中的至少一个包括限定在其中的至少一个凹槽（80），至少一个凹槽包括至少一个加工面（86），以及用于将凹槽接合至少一个加工面的保持器将可变叶片耦合在燃气涡轮发动机内，保持器构造成便于减少可变叶片的磨损。

10. 发明公开

EP1101947A2 Rub resistant compressor stage 有权
标题翻译：。。。
公开(公告)号：EP1101947A2
公开(公告)日：2001-05-23
申请号：EP00307007.5
申请日：2000-08-16
申请人： GENERAL ELECTRIC COMPANY
发明人： Mielke, Mark Joseph , Carroll, Michael David , Marusko, Mark Willard , Rhoda, James Edwin , Bulman, David Edward
IPC分类号： F04D29/16 , F01D11/08
CPC分类号： F04D29/164 , F01D11/08 , F04D29/526 , F04D29/685 , F05D2240/11 , Y10S415/914
摘要： A compressor casing (34) is configured to surround blade tips (24) in a compressor stage. The casing includes stall grooves (36) with adjoining lands (38) defining respective local gaps with the blade tips. At least one of the lands (38a) is offset to locally increase (B) a corresponding one of the gaps larger than the nominal gap (A) for the casing to reduce tip rubbing thereat.
摘要翻译：压缩机壳体（34）构造成围绕压缩机级的叶片尖端（24）。壳体包括具有与刀片尖端限定相应的局部间隙的相邻平台（38）的失速槽（36）。至少一个焊盘（38a）偏移以局部地增加（B）大于用于壳体的标称间隙（A）的相应的一个间隙，以减少其上的尖端摩擦。

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