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71. 发明申请

US20140219815A1 MULTI-LOBED COOLING HOLE 有权
标题翻译：多孔冷却孔
公开(公告)号：US20140219815A1
公开(公告)日：2014-08-07
申请号：US13629916
申请日：2012-09-28
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Atul Kohli , Matthew S. Gleiner
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/186 , F01D5/187 , F01D9/065 , F05D2240/81 , F05D2250/73 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe, a second lobe and a transition region. The first lobe diverges longitudinally and laterally from the metering section and has a first shape. The second lobe is generally opposite the first lobe and diverges longitudinally and laterally from the metering section and has a second shape different from the first shape. The transition region is positioned between the first and second lobes and includes a downstream end adjacent the outlet.
摘要翻译：经受高温气体流动的燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。扩散部分包括第一凸角，第二凸角和过渡区域。第一个凸角从计量部分纵向和横向分开并具有第一形状。第二叶片大致与第一叶片相对，并且从计量部分纵向和横向分叉并且具有不同于第一形状的第二形状。过渡区域位于第一和第二凸角之间并且包括邻近出口的下游端。

72. 发明授权

US08777568B2 Apparatus and methods for cooling platform regions of turbine rotor blades 有权
标题翻译：涡轮转子叶片冷却平台区域的装置和方法
公开(公告)号：US08777568B2
公开(公告)日：2014-07-15
申请号：US12894993
申请日：2010-09-30
申请人： Scott Edmond Ellis , John Wesley Harris, Jr. , Adrian Lional Scott
发明人： Scott Edmond Ellis , John Wesley Harris, Jr. , Adrian Lional Scott
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/087 , F05D2230/60 , F05D2230/80 , F05D2240/81 , F05D2250/185 , Y02T50/676 , Y10T29/49336 , Y10T29/49341 , Y10T29/49718 , Y10T29/49721
摘要： A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that in operation, includes at least a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside. The platform cooling arrangement may include: a plate that comprises a plate topside; a channel formed on the plate topside, the channel comprising an upstream end and a downstream end, and being open through the plate topside such that, upon attaching the plate to the platform, the platform underside comprises a channel ceiling; a high-pressure connector that connects the upstream end of the channel to the high-pressure coolant region of the interior cooling passage; and a low-pressure connector that connects the downstream end of the channel to the low-pressure coolant region of the interior cooling passage.
摘要翻译：在涡轮转子叶片中的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，其中转子叶片包括内部冷却通道，其在运行中包括至少高压冷却剂区域和低压冷却剂区域，并且其中所述平台包括平台下侧。平台冷却装置可以包括：板，其包括顶板; 形成在板顶侧的通道，所述通道包括上游端和下游端，并且通过所述板顶部开口，使得在将所述板附接到所述平台时，所述平台下侧包括通道顶板; 高压连接器，其将通道的上游端连接到内部冷却通道的高压冷却剂区域; 以及将通道的下游端连接到内部冷却通道的低压冷却剂区域的低压连接器。

73. 发明授权

US08763402B2 Multi-lobed cooling hole and method of manufacture 有权
标题翻译：多叶冷却孔及制造方法
公开(公告)号：US08763402B2
公开(公告)日：2014-07-01
申请号：US13544090
申请日：2012-07-09
申请人： JinQuan Xu , Mark F. Zelesky , Atul Kohli , Matthew S. Gleiner
发明人： JinQuan Xu , Mark F. Zelesky , Atul Kohli , Matthew S. Gleiner
IPC分类号： F02C1/00
CPC分类号： F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.
摘要翻译：燃气涡轮发动机部件包括冷却孔。冷却孔包括入口，出口，计量部分和扩散部分。扩散部分从计量部分延伸到出口并且包括从计量部分纵向和横向发散的第一凸角，邻近第一凸角并从计量部分纵向和横向发散的第二凸角，以及过渡区域，其具有在第一和第二凸角之间延伸，并且邻近出口延伸。

74. 发明申请

US20140154063A1 AIRFOIL AND A METHOD FOR COOLING AN AIRFOIL PLATFORM 有权
标题翻译： AIRFOIL和一种冷却气翼平台的方法
公开(公告)号：US20140154063A1
公开(公告)日：2014-06-05
申请号：US13705804
申请日：2012-12-05
申请人： GENERAL ELECTRIC COMPANY
发明人： Xiuzhang James Zhang , Stephen Paul Wassynger , Aaron Ezekiel Smith , Anthony Louis Giglio
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： An airfoil includes an outer surface having a leading edge, a trailing edge downstream from the leading edge, and a convex surface between the leading and trailing edges. A cavity is inside the outer surface, and a platform is connected to the outer surface and defines a top surface around at least a portion of the outer surface. A first plurality of trenches is beneath the top surface of the platform upstream from the leading edge, wherein each trench in the first plurality of trenches is in fluid communication with the cavity inside the outer surface. A first plurality of cooling passages provide fluid communication from the first plurality of trenches through the top surface of the platform.
摘要翻译：翼型件包括具有前缘的外表面，在前缘下游的后缘以及前缘和后缘之间的凸面。空腔在外表面内，并且平台连接到外表面并且围绕外表面的至少一部分限定顶表面。第一多个沟槽位于平台的顶表面上方的前缘上游，其中第一多个沟槽中的每个沟槽与外表面内的空腔流体连通。第一多个冷却通道提供从第一多个沟槽通过平台的顶表面的流体连通。

75. 发明授权

US08714909B2 Platform with cooling circuit 有权
标题翻译：平台带冷却回路
公开(公告)号：US08714909B2
公开(公告)日：2014-05-06
申请号：US12975416
申请日：2010-12-22
申请人： Tracy A. Propheter-Hinckley
发明人： Tracy A. Propheter-Hinckley
IPC分类号： F01D5/18
CPC分类号： F01D9/041 , F01D11/24 , F05D2230/21 , F05D2230/232 , F05D2240/11 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/205 , F05D2260/2212 , F05D2260/22141
摘要： A turbine engine component has an airfoil portion, which airfoil portion is bounded by a platform at one end. The platform has an as-cast open cavity bordered by at least one as-cast landing. A plate is welded to the at least one as-cast landing to cover and close the as-cast open cavity. A process for forming the turbine engine component is described.
摘要翻译：涡轮发动机部件具有翼型部分，翼型部分在一端由平台限定。该平台具有由至少一个演员着陆界定的演习开放空腔。板被焊接到至少一个铸造着陆部以覆盖和关闭铸态开放腔。描述了用于形成涡轮发动机部件的过程。

76. 发明申请

US20140116666A1 Film Cooling Channel Array Having Anti-Vortex Properties 有权
标题翻译：具有抗涡流特性的薄膜冷却通道阵列
公开(公告)号：US20140116666A1
公开(公告)日：2014-05-01
申请号：US13660148
申请日：2012-10-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： JinQuan Xu
IPC分类号： F28F3/12
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
摘要： A cooling channel array carried by a component wall of a gas turbine engine is provided. The cooling channel array comprises a diffusion cavity and a metering section. The metering section comprises a main hole and two or more side holes. The side holes may be separate from the main hole or may branch off of the main hole. The diffusion cavity may incorporate a lobed configuration to help diffuse cooling fluid as it exits the cooling channel array.
摘要翻译：提供了由燃气涡轮发动机的部件壁承载的冷却通道阵列。冷却通道阵列包括扩散腔和计量部。计量部分包括主孔和两个或更多个侧孔。侧孔可以与主孔分离，或者可以从主孔分支。扩散腔可以包括叶形结构，以帮助冷却流体在离开冷却通道阵列时扩散。

77. 发明授权

US08689568B2 Cooling hole with thermo-mechanical fatigue resistance 有权
标题翻译：冷却孔具有耐热机械疲劳性
公开(公告)号：US08689568B2
公开(公告)日：2014-04-08
申请号：US13544097
申请日：2012-07-09
申请人： Atul Kohli , Matthew S. Gleiner , Mark F. Zelesky , JinQuan Xu
发明人： Atul Kohli , Matthew S. Gleiner , Mark F. Zelesky , JinQuan Xu
IPC分类号： F02C7/12
CPC分类号： F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.
摘要翻译：燃气涡轮发动机包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。扩散部分包括从计量部分纵向和横向分叉的第一凸角，从计量部分纵向和横向分开的第二凸角，位于出口处的上游端，位于与上游端相对的出口处的后缘，第一和第二侧壁。每个侧壁具有沿着上游端和后缘之间的出口延伸的边缘。每个边缘从上游端横向分开，并在到达后缘之前横向会聚。

78. 发明授权

US08684664B2 Apparatus and methods for cooling platform regions of turbine rotor blades 有权
标题翻译：涡轮转子叶片冷却平台区域的装置和方法
公开(公告)号：US08684664B2
公开(公告)日：2014-04-01
申请号：US12895035
申请日：2010-09-30
申请人： John Wesley Harris, Jr. , Scott Edmond Ellis , Xiaoyong Fu , Adrian Lional Scott
发明人： John Wesley Harris, Jr. , Scott Edmond Ellis , Xiaoyong Fu , Adrian Lional Scott
IPC分类号： F01D5/08
CPC分类号： F01D5/081 , F01D5/186 , F05D2240/81 , Y02T50/676
摘要： A platform cooling configuration in a turbine rotor blade that includes platform slot formed through at least one of the pressure side slashface and the suction side slashface; a removably-engaged impingement insert that separates the platform into two radially stacked plenums, a first plenum that resides inboard of a second plenum; a high-pressure connector that connects the first plenum to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the second plenum to the low-pressure coolant region of the interior cooling passage.
摘要翻译：涡轮转子叶片中的平台冷却结构，其包括通过压力侧斜面和吸力侧斜面中的至少一个形成的平台槽; 可拆卸地接合的冲击插入件，其将平台分离成两个径向堆叠的通风室，第一增压室位于第二增压室内; 将第一增压室连接到内部冷却通道的高压冷却剂区域的高压连接器; 将第二增压室连接到内部冷却通道的低压冷却剂区域的低压连接器。

79. 发明授权

US08668440B2 Platform segment for supporting a nozzle guide vane for a gas turbine and nozzle guide vane arrangement for a gas turbine 有权
标题翻译：用于支撑用于燃气轮机的喷嘴导向叶片和用于燃气轮机的喷嘴导向叶片装置的平台段
公开(公告)号：US08668440B2
公开(公告)日：2014-03-11
申请号：US13703643
申请日：2011-05-31
申请人： David Butler , Anthony Davis , Charlotte Poole , Paul Mathew Walker
发明人： David Butler , Anthony Davis , Charlotte Poole , Paul Mathew Walker
IPC分类号： F01D5/08
CPC分类号： F01D9/023 , F01D9/041 , F05D2240/127 , F05D2240/81 , F05D2260/201 , F05D2260/2212
摘要： A platform segment for supporting a nozzle guide vane for a gas turbine is provided. The platform segment includes a gas passage surface arranged to be in contact with a streaming gas exhausted from a combustor, wherein the streaming gas streams along the gas passage surface in a streaming direction, a cooling surface, opposite to and thermally connected to the gas passage surface and arranged to be in contact with a cooling fluid, a wall protruding from the cooling surface and extending at least partially in the streaming direction, wherein the wall is arranged circumferentially between positions, at which adjacent guide vanes are to be provided, such that cooling fluid is channeled by the wall for cooling a downstream portion of the cooling surface, and a further wall protruding from the cooling surface and extending at least partially in the streaming direction.
摘要翻译：提供了一种用于支撑用于燃气轮机的喷嘴导向叶片的平台段。所述平台段包括气体通道表面，其布置成与从燃烧器排出的流动气体接触，其中所述流动气体沿流动方向沿所述气体通道表面流动，冷却表面与所述气体通道相对并热连接表面并布置成与冷却流体接触，壁从冷却表面突出并且至少部分地沿流动方向延伸，其中壁在周向上布置在相邻导向叶片的位置之间，使得冷却流体由壁引导，用于冷却冷却表面的下游部分，以及从冷却表面突出并在流动方向上至少部分延伸的另一壁。

80. 发明申请

US20140047844A1 GAS TURBINE ENGINE COMPONENT HAVING PLATFORM TRENCH 审中-公开
标题翻译：气体涡轮发动机组件具有平台倾斜
公开(公告)号：US20140047844A1
公开(公告)日：2014-02-20
申请号：US13585274
申请日：2012-08-14
申请人： Bret M. Teller , Mark F. Zelesky , Scott D. Lewis , Brandon W. Spangler , Ricardo Trindade
发明人： Bret M. Teller , Mark F. Zelesky , Scott D. Lewis , Brandon W. Spangler , Ricardo Trindade
IPC分类号： F01D25/12 , F02C3/04
CPC分类号： F01D5/187 , F01D11/24 , F05D2240/11 , F05D2240/81 , F05D2260/201 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间轴向延伸并在第一配合面和第二配合面之间周向延伸的平台，沟槽，设置在第一配合面和第二配合面中的至少一个上。多个冷却孔轴向设置在沟槽内。

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