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1. 发明授权

US06802690B2 Outlet silencer structures for turbine 失效
标题翻译：汽轮机出口消声器结构
公开(公告)号：US06802690B2
公开(公告)日：2004-10-12
申请号：US10301279
申请日：2002-11-21
申请人： Ming Hui Han , Muammer Yazici
发明人： Ming Hui Han , Muammer Yazici
IPC分类号： F01D2504
CPC分类号： F01D25/30 , F02C7/045 , F04D29/664 , F05D2250/50 , F05D2260/96
摘要： Both air duct inlet silencers and air duct outlet silencers for use with a stationary gas turbine are disclosed. The sound attenuating duct unit suitable for connecting to an outlet of a stationary gas turbine includes a housing having a horizontal housing section and a vertical housing section and having sidewalls surrounding a main airflow passageway that extends along a substantial bend. An air inlet is located at one end of the horizontal housing section and is adapted for connection to the outlet of the gas turbine. Preferably two air outlets are located proximate to an upper end of the vertical housing section. Splitters are mounted in the housing, and they divide sections of the main airflow passageway into smaller air passageways. At least one of the splitters is positioned upstream in the main airflow passageway relative to other splitters. The splitters contain sound attenuating material capable of withstanding airflow temperatures in the main airflow passageway of at least 500 degrees Celsius. At least a substantial portion of both the sidewalls surrounding the main airflow passageway and metal sidewalls forming the splitters are made of perforated sheet metal.
摘要翻译：公开了用于固定式燃气轮机的两个空气管道入口消音器和空气管道出口消音器。适于连接到静止燃气轮机的出口的声音衰减管道单元包括具有水平壳体部分和垂直壳体部分的壳体，并且具有围绕沿主要弯曲部延伸的主气流通道的侧壁。空气入口位于水平壳体部分的一端并且适于连接到燃气轮机的出口。优选地，两个空气出口位于垂直容纳部分的上端附近。分流器安装在壳体中，并且它们将主气流通道的部分分成更小的空气通道。分流器中的至少一个相对于其他分离器位于主气流通道的上游。分离器包含能够承受至少500摄氏度的主气流通道中的气流温度的声音衰减材料。围绕主气流通道的两个侧壁和形成分离器的金属侧壁的至少大部分由多孔金属板制成。

2. 发明申请

US20030072648A1 Outlet silencer structures for turbine 失效
标题翻译：汽轮机出口消声器结构
公开(公告)号：US20030072648A1
公开(公告)日：2003-04-17
申请号：US10301279
申请日：2002-11-21
发明人： Ming Hui Han , Muammer Yazici
IPC分类号： F01D005/10
CPC分类号： F01D25/30 , F02C7/045 , F04D29/664 , F05D2250/50 , F05D2260/96
摘要： Both air duct inlet silencers and air duct outlet silencers for use with a stationary gas turbine are disclosed. The sound attenuating duct unit suitable for connecting to an outlet of a stationary gas turbine includes a housing having a horizontal housing section and a vertical housing section and having sidewalls surrounding a main airflow passageway that extends along a substantial bend. An air inlet is located at one end of the horizontal housing section and is adapted for connection to the outlet of the gas turbine. Preferably two air outlets are located proximate to an upper end of the vertical housing section. Splitters are mounted in the housing, and they divide sections of the main airflow passageway into smaller air passageways. At least one of the splitters is positioned upstream in the main airflow passageway relative to other splitters. The splitters contain sound attenuating material capable of withstanding airflow temperatures in the main airflow passageway of at least 500 degrees Celsius. At least a substantial portion of both the sidewalls surrounding the main airflow passageway and metal sidewalls forming the splitters are made of perforated sheet metal.
摘要翻译：公开了用于固定式燃气轮机的两个空气管道入口消音器和空气管道出口消音器。适于连接到静止燃气轮机的出口的声音衰减管道单元包括具有水平壳体部分和垂直壳体部分的壳体，并且具有围绕沿主要弯曲部延伸的主气流通道的侧壁。空气入口位于水平壳体部分的一端并且适于连接到燃气轮机的出口。优选地，两个空气出口位于垂直容纳部分的上端附近。分流器安装在壳体中，并且它们将主气流通道的部分分成更小的空气通道。分流器中的至少一个相对于其他分离器位于主气流通道的上游。分离器包含能够承受至少500摄氏度的主气流通道中的气流温度的声音衰减材料。围绕主气流通道的两个侧壁和形成分离器的金属侧壁的至少大部分由多孔金属板制成。

3. 发明申请

US20020182061A1 Air inlet and outlet silencer structures for turbine 失效
标题翻译：涡轮机进气和出口消声器结构
公开(公告)号：US20020182061A1
公开(公告)日：2002-12-05
申请号：US09867982
申请日：2001-05-30
发明人： Ming Hui Han
IPC分类号： F01D025/00
CPC分类号： F04D29/664 , F01D25/30 , F02C7/045 , F05D2250/50 , F05D2260/96
摘要： Both air duct inlet silencers and air duct outlet silencers for use with a stationary gas turbine are disclosed. The inlet silencer comprises a vertically extending duct structure having an upper section with a plurality of vertically extending sides and a top cover. Air inlet openings are formed in the vertically extending sides and an air outlet is formed at the bottom end for connection to the air intake housing of the turbine. An elongate, central airflow defining member is substantially cylindrical for a major portion of its length and extends downwardly from the top cover and past the air inlets. This member has a perforated sheet metal exterior and contains sound attenuating material. Airflow passages extend from the inlet openings towards the outlet with each defined by at least one interior wall. Each passageway bends substantially downwardly so that the bottom section extends vertically. The outlet silencer includes first and second series of splitters with each series forming smaller air passageways.
摘要翻译：公开了用于固定式燃气轮机的两个空气管道入口消音器和空气管道出口消音器。入口消音器包括垂直延伸的管道结构，其具有具有多个垂直延伸的侧面和顶盖的上部部分。空气入口开口形成在垂直延伸的侧面，并且在底端处形成空气出口以连接到涡轮机的进气口。细长的中央气流限定构件在其长度的大部分上基本上是圆柱形的并且从顶盖向下延伸并且经过空气入口。该构件具有穿孔的金属板外部并且包含声音衰减材料。气流通道从入口开口朝向出口延伸，每个由至少一个内壁限定。每个通道基本上向下弯曲，使得底部部分垂直延伸。出口消音器包括第一和第二系列分离器，每个系列形成较小的空气通道。

4. 发明授权

US09181961B1 Compressor intake noise prevention by choking flow with duct geometry 有权
标题翻译：压缩机进气噪音通过阻塞流动与导管几何形状
公开(公告)号：US09181961B1
公开(公告)日：2015-11-10
申请号：US14623897
申请日：2015-02-17
申请人： BorgWarner Inc.
发明人： Evan Lucas , Sean Hastings
IPC分类号： F04D21/00 , F04D29/46 , F04D29/66 , F04D17/10 , F01D17/14 , F02B37/00 , F04D27/02
CPC分类号： F01D17/14 , F01D9/026 , F01D17/146 , F01D25/24 , F02B37/00 , F04D17/10 , F04D21/00 , F04D27/0246 , F04D27/0253 , F04D29/462 , F04D29/464 , F04D29/667 , F05D2220/40 , F05D2250/50 , F05D2250/51 , F05D2260/96
摘要： A number of variations may include a product for use with a turbocharger system may include a compressor wheel for charging a flow stream. A housing may be disposed around the compressor wheel, defining an inlet passage and a discharge passage. The flow stream may extend through the inlet passage, around the compressor wheel and through the outlet passage. The inlet passage may be configured to impart a supersonic speed to the flow stream to inhibit sound from propagating against the flow stream through the inlet passage.
摘要翻译：许多变型可以包括用于涡轮增压器系统的产品可以包括用于对流动流充电的压缩机叶轮。壳体可以设置在压缩机叶轮周围，限定入口通道和排出通道。流动流可以延伸穿过入口通道，围绕压缩机叶轮并通过出口通道。入口通道可以被配置成赋予流动流超音速以阻止声音抵抗通过入口通道的流动流传播。

5. 发明授权

US08448451B2 Height ratios for a transition piece of a combustor 有权
标题翻译：燃烧器过渡件的高度比
公开(公告)号：US08448451B2
公开(公告)日：2013-05-28
申请号：US12674352
申请日：2009-04-23
申请人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
发明人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
IPC分类号： F02C3/04 , F02C1/00
CPC分类号： F01D9/023 , F05D2250/50 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02E20/16 , Y10T29/49229 , Y10T29/49348
摘要： Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79≦Dout/Din≦0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.
摘要翻译：提供了一种燃烧器连接结构，其中过渡件出口的横截面积（Dout）相对于过渡件入口的横截面面积（Din）设定在0.79 @ Dout / Din @ 0.9的范围内并且在连接到过渡件出口的涡轮机的第一级涡轮喷嘴中，在内护罩和外护罩的上游端之间的径向方向上的尺寸（Hin）具有与尺寸相同的尺寸（a ）在过渡件出口的径向方向上。在包括在具有与燃气轮机的转子的轴向中心（R）成一角度的中心线（S））并且将燃烧气体引导到涡轮机的燃烧器中的燃烧器过渡件中，横截面积从燃烧气体流过到燃烧气体流出的过渡件出口的过渡件入口单调地减少。

6. 发明授权

US07520724B2 Cooled blade for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片
公开(公告)号：US07520724B2
公开(公告)日：2009-04-21
申请号：US11483091
申请日：2006-07-10
申请人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/081 , F05D2250/50 , F05D2260/205 , F05D2260/221
摘要： A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct. An orifice can, for example, extend from the main coolant inlet to the second deflection region.
摘要翻译：用于燃气涡轮机的冷却叶片具有叶片翼型件，叶片翼型件从叶片根部和叶片柄部突出并且具有前缘和后缘，并且在叶片翼型件内，在流动方面，多个顺序的冷却剂管道，沿径向延伸。沿着前缘的第一冷却剂管道和沿着后缘的第二冷却剂管道具有从叶片根部到叶片翼型的尖端流过它们的冷却剂的主流。第一冷却剂管道的入口与主冷却剂入口连接，并且第一冷却剂管道的出口经由第一偏转区域与第二冷却剂管道的入口连接。第三冷却剂管道布置在第一和第二冷却剂管道和第二偏转区域之间。从外部提供的另外冷却剂冷却流从第三冷却剂管道加入流入第二冷却剂管道的冷却剂的加热主流。孔可以例如从主冷却剂入口延伸到第二偏转区域。

7. 发明申请

US20080121301A1 Externally Mounted Vortex Generators for Flow Duct Passage 有权
标题翻译：用于流道通道的外置涡旋发电机
公开(公告)号：US20080121301A1
公开(公告)日：2008-05-29
申请号：US11547527
申请日：2005-04-06
申请人： Thomas R. Norris
发明人： Thomas R. Norris
IPC分类号： F15D1/02
CPC分类号： F02C7/04 , F01D25/30 , F05D2250/50 , F05D2260/22141 , Y02T50/675
摘要： A high drag vortex generator for inhibiting the formation of boundary layer gas flow is mounted in a duct having a strong adverse pressure gradient with high speed gas flow over a primary aerodynamic. The vortex generator includes a mounting for supporting the high drag vortex generator at a spatial interval in the high speed gas flow above the primary aerodynamic surface. The high drag vortex generator is supported from the mounting and extends from the mounting in the high speed gas flow less than the full distance to the primary aerodynamic surface. Each high drag vortex generator includes first and second vanes. The first and second vanes have flow confining components at substantial right angles to one another. The vanes flow confining components deflect fluid flow towards and/or away from the primary aerodynamic surface inhibiting boundary layer formation downstream of the vortex generator.
摘要翻译：用于抑制边界层气体流动形成的高阻力涡流发生器安装在具有强的不利压力梯度的管道中，在主空气动力学上具有高速气流。涡流发生器包括用于在主空气动力学表面上方的高速气流中以空间间隔支撑高阻力涡流发生器的安装件。高阻力涡流发生器从安装座支撑，并从低于全距离的高速气流中的安装件延伸到主空气动力学表面。每个高阻涡流发生器包括第一和第二叶片。第一和第二叶片具有彼此基本成直角的流动限制部件。叶片流动限制部件使流体流向和/或远离涡流发生器下游的主要空气动力学表面抑制边界层形成。

8. 发明申请

US20190211692A1 GAS TURBINE ENGINE COMPONENTS HAVING INTERNAL HYBRID COOLING CAVITIES 审中-公开
公开(公告)号：US20190211692A1
公开(公告)日：2019-07-11
申请号：US15864456
申请日：2018-01-08
申请人： United Technologies Corporation
发明人： Dominic J. Mongillo, JR.
IPC分类号： F01D5/18 , F01D9/04 , F01D11/08 , F01D25/12 , F23R3/04 , F02C7/18
CPC分类号： F01D5/187 , F01D25/12 , F05D2220/32 , F05D2240/35 , F05D2250/50 , F05D2250/71 , F05D2260/202 , F05D2260/204 , F05D2260/2212 , F05D2260/22141 , F23R2900/03045
摘要： Components for gas turbine engines are provided. The components include a hybrid skin core cooling cavity defined by a cold wall and a hot wall, wherein the hot wall is exposed to an exterior environment of the component and a resupply hole is formed in the cold wall and fluidly connects a cold core cavity and the cooling cavity. The resupply hole extends between an inlet on a side of the cold wall exposed to the cold core cavity and an outlet on a side of the cold wall exposed to the cooling cavity. The cavity resupply hole is angled relative to the cold wall at an injection angle such that air passing through the cavity resupply hole is injected into the cooling cavity at the injection angle and at least partially parallel to a direction of flow within the hybrid skin core cooling cavity.

9. 发明申请

US20130052037A1 AIRFOIL WITH NONLINEAR COOLING PASSAGE 审中-公开
标题翻译：非线性冷却通风机
公开(公告)号：US20130052037A1
公开(公告)日：2013-02-28
申请号：US13222490
申请日：2011-08-31
申请人： William Abdel-Messeh , Justin D. Piggush
发明人： William Abdel-Messeh , Justin D. Piggush
IPC分类号： F01D5/18 , B22C9/10 , B22D25/02
CPC分类号： F01D5/186 , B22C9/103 , F01D5/187 , F05D2250/50 , F05D2250/70 , F05D2260/204 , F05D2260/221
摘要： An example method of manufacturing an airfoil includes providing a ceramic core corresponding to an interior cooling channel. A refractory metal core is provided that corresponds to a cooling passage. The cores are arranged in a mold. An airfoil structure is cast about the cores to provide a turbine engine airfoil. The turbine engine airfoil includes a wall providing the interior cooling channel and an exterior airfoil surface. The cooling passage is provided in the wall and fluidly connects the interior cooling channel to the exterior airfoil surface. The cooling passage includes multiple inlets and multiple outlets respectively adjoining the interior cooling channel and the exterior airfoil surface. At least one of a first inlet and outlet has a different structural flow characteristic than at least one of a second inlet and outlet.
摘要翻译：制造翼型的示例性方法包括提供对应于内部冷却通道的陶瓷芯。提供对应于冷却通道的难熔金属芯。核心布置在模具中。翼型结构围绕芯铸造以提供涡轮发动机翼型件。涡轮发动机翼型件包括提供内部冷却通道和外部翼型件表面的壁。冷却通道设置在壁中并将内部冷却通道流体连接到外部翼型表面。冷却通道包括分别邻接内部冷却通道和外部翼型表面的多个入口和多个出口。第一入口和出口中的至少一个具有与第二入口和出口中的至少一个不同的结构流动特性。

10. 发明申请

US20110265491A1 COMBUSTOR CONNECTION STRUCTURE, COMBUSTOR TRANSITION PIECE, DESIGNING METHOD OF COMBUSTOR TRANSITION PIECE, AND GAS TURBINE 有权
标题翻译： COMBUSTOR连接结构，COMBUSTOR过渡片，COMBUSTOR TRANSITION PIECE和燃气轮机的设计方法
公开(公告)号：US20110265491A1
公开(公告)日：2011-11-03
申请号：US12674352
申请日：2009-04-23
申请人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
发明人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
IPC分类号： F02C7/20 , G06F17/50
CPC分类号： F01D9/023 , F05D2250/50 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02E20/16 , Y10T29/49229 , Y10T29/49348
摘要： Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet (222) is set within a range of 0.79≦Dout/Din≦0.9, relative to a cross-sectional area (Din) of a transition piece inlet (221) of a combustor (2), and in a first stage turbine nozzle (321) of a turbine (3) connected to the transition piece outlet (222), a size (Hin) in a radial direction of an upstream opening is matched with a size (a) in a radial direction of the transition piece outlet (222). In a combustor transition piece (22) that is included in the combustor (2) having a center line (S) arranged with an angle to an axial center (R) of a rotor (4) of a gas turbine and that guides combustion gas to the turbine (3), a cross-sectional area is monotonously reduced from the transition piece inlet (221) in which the combustion gas flows to the transition piece outlet (222) from which the combustion gas flows out.
摘要翻译：提供了一种燃烧器连接结构，其中过渡件出口（222）的横截面面积（Dout）设定在0.79

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