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11. 发明授权

US09464528B2 Cooled turbine blade with double compound angled holes and slots 有权
标题翻译：具有双组合倾斜孔和槽的冷却涡轮叶片
公开(公告)号：US09464528B2
公开(公告)日：2016-10-11
申请号：US13918052
申请日：2013-06-14
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/304 , F05D2250/314 , F05D2250/324 , F05D2260/202
摘要： A turbine blade for a gas turbine engine. The turbine blade includes a base having a blade root, a platform, a cooling air inlet, and a base air passageway. The turbine blade also includes an airfoil section adjoined to the base and having an outer wall, an airfoil air passageway, a plurality of trailing edge slots in fluid communication with the airfoil air passageway and a plurality of directional film holes through the outer wall in fluid communication with the airfoil air passageway. The plurality of directional film holes includes a first portion configured to discharge the cooling air toward a tip end, and a second portion configured to discharge the cooling air toward the platform.
摘要翻译：一种用于燃气涡轮发动机的涡轮叶片。涡轮叶片包括具有叶片根部，平台，冷却空气入口和基部空气通道的底座。涡轮机叶片还包括邻接于基座的翼型部分，并且具有外壁，翼型空气通道，与翼型空气通道流体连通的多个后缘槽和通过流体的外壁的多个定向膜孔与翼型通风通道。多个定向膜孔包括构造成朝向顶端排出冷却空气的第一部分和被构造成朝向平台排出冷却空气的第二部分。

12. 发明申请

US20160245119A1 TURBOCHARGER DIFFUSER CENTER BODY 审中-公开
标题翻译： TURBOCHARGER DIFFUSER中心体
公开(公告)号：US20160245119A1
公开(公告)日：2016-08-25
申请号：US14631639
申请日：2015-02-25
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Christopher W. Wilkins , Wagner M. Magalhaes , Bharathi Raja Sugumaran , Martin Babak
IPC分类号： F01D25/24 , F01D5/02 , F02B33/40 , F01D9/04 , F02B37/00
CPC分类号： F01D25/24 , F01D5/02 , F01D9/02 , F01D9/041 , F01D17/105 , F01D25/30 , F02B33/40 , F02B37/00 , F02B37/18 , F05D2220/40 , F05D2240/12 , F05D2240/14 , F05D2240/24 , F05D2250/324 , Y02T10/144
摘要： A turbocharger turbine having housing walls defining a diffuser. Within the diffuser, a center body within the diffuser is supported by de-swirl vanes extending from the diffuser wall. The center body forms a de-swirl passageway having an increasing mean diameter of flow from an upstream end of the center body to a leading edge of the de-swirl vanes. A trailing edge of the de-swirl vanes is near the downstream end of the center body. Annular-type guide vanes surround the center body within the de-swirl passageway. A wastegate system is configured to vent wastegate flow into the diffuser through injection ports on the de-swirl vanes, annular guide vanes and/or center body.
摘要翻译：一种具有限定扩散器的壳体壁的涡轮增压器涡轮机。在扩散器内，扩散器内的中心体由从扩散壁延伸的去旋转叶片支撑。中心体形成具有从中心体的上游端到脱流叶片的前缘的流动平均直径增加的去涡流通道。脱流叶片的后缘靠近中心体的下游端。环形导叶围绕脱气通道内的中心体。废气门系统被配置成通过在旋流叶片，环形引导叶片和/或中心体上的注射口将排气门流入扩散器。

13. 发明申请

US20160169002A1 AIRFOIL TRAILING EDGE TIP COOLING 审中-公开
标题翻译： AIRFOIL拖车边缘冷却
公开(公告)号：US20160169002A1
公开(公告)日：2016-06-16
申请号：US14908664
申请日：2014-07-24
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Wieslaw A. CHLUS , Seth J. THOMEN
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/186 , F01D5/187 , F01D5/20 , F02C7/18 , F05D2240/304 , F05D2240/307 , F05D2250/324 , F05D2260/202
摘要： An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body that includes a first wall and a second wall spaced apart and joined together at each of a leading edge and a trailing edge and extending between a root and a tip. An internal cooling circuit is disposed at least partially inside of the airfoil body. The internal cooling circuit has a first cooling passage disposed near a junction between the tip and the trailing edge and a fanned array of cooling holes that extend between the first cooling passage to at least the tip.
摘要翻译：根据本公开的示例性方面的翼型件包括除了别的以外的翼型件主体，其包括第一壁和第二壁，所述第一壁和第二壁在前缘和后缘中的每一个处间隔开并连接在一起，并且在根部和一个提示。内部冷却回路至少部分地设置在翼型体内部。内部冷却回路具有设置在尖端和后缘之间的接合点附近的第一冷却通道，以及在第一冷却通道之间延伸至至少尖端的扇形排列的冷却孔。

14. 发明授权

US09341120B2 Channeled spring seal for sealing an air gap between moving plates 有权
标题翻译：用于密封移动板之间的空气间隙的引导弹簧密封
公开(公告)号：US09341120B2
公开(公告)日：2016-05-17
申请号：US13371074
申请日：2012-02-10
申请人： Thomas M. Barry, Jr. , Corina Scanio
发明人： Thomas M. Barry, Jr. , Corina Scanio
IPC分类号： F02K1/00 , F02C7/28 , F02K1/80
CPC分类号： F02C7/28 , F02K1/002 , F02K1/805 , F05D2240/57 , F05D2250/324 , F05D2250/713
摘要： A sealed joint may include a first plate with a seal land, a second plate that moves relative to the seal land, and a seal connected to the second plate. The seal may extend laterally between a first seal end and a second seal end. The seal may include a plurality of seal elements that extend longitudinally between a first seal side and a second seal side. A first of the seal elements may extend laterally from the first seal end towards a first seal segment, which is separated from the second plate by an airflow channel. The second of the seal elements may extend laterally from the second seal end towards a second seal segment, which is located between and engaged with the first seal segment and the seal land.
摘要翻译：密封接头可以包括具有密封接合面的第一板，相对于密封接合面移动的第二板和连接到第二板的密封件。密封件可以在第一密封端和第二密封端之间横向延伸。密封件可以包括在第一密封侧和第二密封侧之间纵向延伸的多个密封元件。第一密封元件可以从第一密封端横向延伸到第一密封段，第一密封段通过气流通道与第二板隔开。第二密封元件可以从第二密封端侧向第二密封段横向延伸，第二密封段位于第一密封段和密封区之间并与其接合。

15. 发明申请

US20150300367A1 CENTRIFUGAL FAN 审中-公开
标题翻译：离心风扇
公开(公告)号：US20150300367A1
公开(公告)日：2015-10-22
申请号：US14443198
申请日：2014-05-02
申请人： LG ELECTRONICS INC.
发明人： Kyung Jung LEE
IPC分类号： F04D29/42 , F04D29/62 , F04D29/28 , F04D29/44 , F04D17/16 , F04D29/053
CPC分类号： F04D29/4226 , F04D17/16 , F04D29/023 , F04D29/053 , F04D29/281 , F04D29/288 , F04D29/441 , F04D29/626 , F04D29/666 , F05D2230/54 , F05D2250/324 , F05D2250/37 , F05D2250/38 , F05D2250/52 , F05D2300/10
摘要： A centrifugal fan is provided. The centrifugal fan includes a main plate connected to a rotational shaft of a motor, a shroud having a suction opening, through which air is introduced, a plurality of blades arranged between the main plate and the shroud, and a rim formed by bending an outer circumference of at least one of the main plate or the shroud in a longitudinal direction of the rotational shaft, the rim portion having an inclination.
摘要翻译：提供离心风机。离心风扇包括连接到电动机的旋转轴的主板，具有吸入口的罩，空气通过该吸入口，布置在主板和护罩之间的多个叶片，以及通过弯曲外部所述主板或所述护罩中的至少一个在所述旋转轴的纵向方向上的圆周，所述边缘部分具有倾斜度。

16. 发明申请

US20150240667A1 EXHAUST PLENUM FOR RADIAL DIFFUSER 审中-公开
标题翻译：用于径向扩散器的排气孔
公开(公告)号：US20150240667A1
公开(公告)日：2015-08-27
申请号：US14190902
申请日：2014-02-26
申请人： General Electric Company
发明人： Deepesh D. Nanda , Santhosh Kumar Vijayan , Chengappa Manjunath
IPC分类号： F01K23/10 , F01D25/30
CPC分类号： F01K23/10 , F01D25/30 , F05D2250/324 , Y02E20/16
摘要： An exhaust gas diffuser for a turbomachine includes a diffuser supported on a turbine rotor, aligned with an axis of said turbine rotor. The diffuser is configured to re-direct turbine exhaust gas substantially ninety degrees from a first direction of flow along the rotor axis. A plenum chamber is in fluid communication with and surrounds an outlet end of the diffuser. The plenum chamber is in fluid communication with a transition duct adapted to supply the exhaust gas to another turbomachine. The plenum chamber expands in volume between the diffuser and the transition duct.
摘要翻译：用于涡轮机的废气扩散器包括支撑在涡轮机转子上的扩散器，该扩散器与所述涡轮机转子的轴线对齐。扩散器被构造成沿着转子轴线从第一流动方向重新引导涡轮机排气大致九十度。增压室与扩散器的出口端流体连通并围绕扩散器的出口端。增压室与适于将废气供应到另一涡轮机的过渡管道流体连通。增压室在扩散器和过渡管之间的体积膨胀。

17. 发明授权

US09028207B2 Cooled component wall in a turbine engine 有权
标题翻译：在涡轮发动机中冷却的部件壁
公开(公告)号：US09028207B2
公开(公告)日：2015-05-12
申请号：US12888467
申请日：2010-09-23
申请人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
发明人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2230/90 , F05D2250/13 , F05D2250/324 , Y10T29/4935
摘要： A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion.
摘要翻译：涡轮发动机中的部件壁包括基板，扩散部分和至少一个冷却通道。扩散部分位于衬底的表面中并且由第一侧壁和第二侧壁限定。冷却通道包括出口部分，冷却空气通过该出口部分朝向第一侧壁的方向流出。出口部分包括后部，前部和具有近端和远端的内壁。后部位于第一和第二侧壁之间。前部分在第一侧壁和内壁的远端之间延伸。第一侧壁延伸到冷却通道的出口部分到内壁，并从第一侧壁延伸到第二侧壁，以阻挡出口部分的前部。

18. 发明授权

US08978390B2 Cooling hole with crenellation features 有权
标题翻译：冷却孔具有排气功能
公开(公告)号：US08978390B2
公开(公告)日：2015-03-17
申请号：US14204465
申请日：2014-03-11
申请人： United Technologies Corporation
发明人： Glenn Levasseur , Edward F. Pietraszkiewicz
IPC分类号： F01D5/18 , F04D31/00 , F02C7/12 , F01D25/14
CPC分类号： F01D25/14 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2250/182 , F05D2250/183 , F05D2250/324 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676 , Y10T29/49229 , Y10T29/49323
摘要： A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region.
摘要翻译：燃气涡轮发动机的部件的壁包括第一和第二壁表面，位于第一壁表面处的入口，位于第二表面处的出口，从入口开始并从入口的下游延伸的计量部分，以及扩散部分从计量部分延伸并终止在出口处。扩散部分包括形成在出口的上游端的前缘，形成在出口的下游端的后缘，在后缘的上游的身体区域，以及位于身体区域上的多个分类特征。

19. 发明授权

US08961136B1 Turbine airfoil with film cooling hole 有权
标题翻译：涡轮机翼有薄膜冷却孔
公开(公告)号：US08961136B1
公开(公告)日：2015-02-24
申请号：US13397012
申请日：2012-02-15
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/08 , F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/324 , F05D2260/202
摘要： A film cooling hole for an air cooled turbine airfoil, where the film cooling hole includes a first expansion section with expansion only on the downstream wall and a second expansion section with expansion on the downstream wall and the two side walls. No expansion is formed on the upstream walls on the first and second expansion sections.
摘要翻译：一种用于空气冷却涡轮机翼型的薄膜冷却孔，其中薄膜冷却孔包括仅在下游壁上膨胀的第一膨胀部分和在下游壁和两个侧壁上具有膨胀的第二膨胀部分。在第一和第二膨胀部分的上游壁上不形成膨胀。

20. 发明申请

US20140369852A1 COOLED TURBINE BLADE WITH DOUBLE COMPOUND ANGLED HOLES AND SLOTS 有权
标题翻译：冷却涡轮叶片与双重复合角膜和滑枕
公开(公告)号：US20140369852A1
公开(公告)日：2014-12-18
申请号：US13918052
申请日：2013-06-14
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/304 , F05D2250/314 , F05D2250/324 , F05D2260/202
摘要： A turbine blade for a gas turbine engine. The turbine blade includes a base having a blade root, a platform, a cooling air inlet, and a base air passageway. The turbine blade also includes an airfoil section adjoined to the base and having an outer wall, an airfoil air passageway, a plurality of trailing edge slots in fluid communication with the airfoil air passageway and a plurality of directional film holes through the outer wall in fluid communication with the airfoil air passageway. The plurality of directional film holes includes a first portion configured to discharge the cooling air toward a tip end, and a second portion configured to discharge the cooling air toward the platform.
摘要翻译：一种用于燃气涡轮发动机的涡轮叶片。涡轮叶片包括具有叶片根部，平台，冷却空气入口和基部空气通道的底座。涡轮机叶片还包括邻接于基座的翼型部分，并且具有外壁，翼型空气通道，与翼型空气通道流体连通的多个后缘槽和通过流体的外壁的多个定向膜孔与翼型通风通道。多个定向膜孔包括构造成朝向顶端排出冷却空气的第一部分和被构造成朝向平台排出冷却空气的第二部分。

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