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公开(公告)号：US09260972B2
公开(公告)日：2016-02-16
申请号：US13540752
申请日：2012-07-03
CPC分类号： F01D5/18 , F01D5/146 , F01D5/20 , F05D2240/307 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.
摘要翻译： 涡轮机翼片包括抽吸侧壁，压力侧壁，尖端壁和尖端泄漏控制通道。 每个侧壁从翼型基座向翼展方向延伸，并且在前缘和后缘之间并排。 尖端壁从前缘延伸到后缘，并且连接吸力和压力侧壁的相应的外翼展端。 尖端泄漏控制通道具有凹入到顶端壁的外表面中的入口和出口。 通道的入口在翼型压力侧壁和尖端壁的接合点附近开始。 通道的出口终止于尖端壁和抽吸侧壁的接合处的凹陷部分。
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公开(公告)号：US09024226B2
公开(公告)日：2015-05-05
申请号：US13544031
申请日：2012-07-09
申请人： Glenn Levasseur , Edward F. Pietraszkiewicz , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Kevin J. Klinefelter , Stephen D. Doll , Markus W. Fritch
发明人： Glenn Levasseur , Edward F. Pietraszkiewicz , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Kevin J. Klinefelter , Stephen D. Doll , Markus W. Fritch
CPC分类号： B23H9/10 , B23H1/00 , B23H7/26 , B23H9/14 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
摘要： A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.
摘要翻译： 用于形成从壁的第一表面上的入口延伸到壁的第二表面上的出口的冷却孔的方法包括：通过放电加工形成冷却孔的扩散部分和出口上的后缘， 并在扩散段中形成纵向凸起。 计量部分从壁的第一表面上的入口延伸到壁的第二表面。 扩散部分从出口延伸到位于入口和出口之间的计量部分的一端。 出口在后缘处基本上是线性的或凸起的，并且叶片由纵向脊部分开。
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公开(公告)号：US20140271101A1
公开(公告)日：2014-09-18
申请号：US13630681
申请日：2012-09-28
申请人： Thomas N. Slavens , Edward F. Pietraszkiewicz , Thomas J. Martin , Mark F. Zelesky , Steven B. Gautschi , Matthew A. Devore , Alexander Staroselsky
发明人： Thomas N. Slavens , Edward F. Pietraszkiewicz , Thomas J. Martin , Mark F. Zelesky , Steven B. Gautschi , Matthew A. Devore , Alexander Staroselsky
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F01D5/188 , F01D5/189 , F01D9/04 , F01D9/06 , F01D9/065 , F01D17/162 , F05D2220/32 , F05D2240/81 , F05D2260/202 , F05D2260/232 , Y02T50/673 , Y02T50/676
摘要： A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.
摘要翻译： 叶片结构包括可移动地安装在孔内的挡板，所述挡板可移动以控制第一冷却腔和第二冷却腔之间的冷却流。
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公开(公告)号：US20140000282A1
公开(公告)日：2014-01-02
申请号：US13537258
申请日：2012-06-29
申请人： Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Scott D. Lewis , Jeffrey S. Beattie , Jeffrey Michael Jacques , Brandon M. Rapp
发明人： Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Scott D. Lewis , Jeffrey S. Beattie , Jeffrey Michael Jacques , Brandon M. Rapp
CPC分类号： F01D5/085 , F01D5/081 , F01D5/18 , F05D2240/81 , Y02T50/676
摘要： A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.
摘要翻译： 用于燃气涡轮发动机的涡轮机叶片包括一个翼型件，其包括通过间隔开的压力和吸力侧面连接的前缘和后缘，以提供在径向方向上延伸的外部翼面。 后缘设置在涡轮叶片的后侧。 根部支撑翼型件延伸的平台，并且冷却通道在根部内在径向方向上延伸到翼型件。 下翼设置在平台的后侧，在轴向方向上延伸，以提供具有沿圆周方向延伸的平台的U形通道。 冲击孔从U形通道延伸到冷却通道。
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公开(公告)号：US06283708B1
公开(公告)日：2001-09-04
申请号：US09453649
申请日：1999-12-03
申请人： Mark F. Zelesky
发明人： Mark F. Zelesky
IPC分类号： B63H114
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202 , Y02T50/67 , Y02T50/676
摘要： A coolable vane (12) for a turbomachine includes an airfoil (16) with a pair of imperforate ribs (42, 44) that extend laterally across the airfoil. The ribs have suction side termini (52, 56) and pressure side termini (54, 58). The suction side termini chordwisely delimit a segment SS of the airfoil suction wall (28) so that the ribs and the suction wall segment bound an internal plenum (48) for distributing a pressurized coolant spanwisely through the interior of the airfoil. An array of film cooling holes (84) penetrates the suction wall segment and is the exclusive avenue for conveying coolant from the plenum to a working medium fluid flowpath. Accordingly, relatively low pressure coolant may be supplied to the plenum without the risk of backflow or spanwise discontinuities in the surface cooling film. In one specific embodiment of the invention, the suction side rib termini (52, 56) straddle a point of minimum fluid pressure along the suction surface (38) so that positive coolant flow and spanwise continuity of the cooling film can be realized with coolant of the lowest possible pressure and without exposing the suction wall segment SS to excessive stress.
摘要翻译： 用于涡轮机的可冷却叶片（12）包括翼型件（16），其具有横跨翼型延伸的一对无孔肋条（42,44）。 肋具有吸入侧端部（52,56）和压力侧端子（54,58）。 吸入侧端部弦向地限定翼型件抽吸壁（28）的段SS，使得肋和抽吸壁段结合内部增压室（48），用于将加压的冷却剂分流穿过翼型件的内部。 一组薄膜冷却孔（84）穿透吸壁部分，是将冷却剂从气室输送到工作介质流体流路的专用通道。 因此，可以将相对低压的冷却剂供应到集气室，而不会在表面冷却膜中产生回流或翼展方向不连续的风险。 在本发明的一个具体实施例中，吸入侧肋端部（52,56）沿着吸力表面（38）跨过最小流体压力点，使得冷却剂流的正向冷却剂流动和翼展方向连续性可以通过 压力尽可能低，并且不会使吸力壁段SS暴露于过度的压力。
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公开(公告)号：US5800124A
公开(公告)日：1998-09-01
申请号：US631506
申请日：1996-04-12
申请人： Mark F. Zelesky
发明人： Mark F. Zelesky
CPC分类号： F01D5/081 , F01D11/006 , F01D5/3015 , F05D2240/81 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A cooled rotor assembly for a gas turbine engine includes rotor blades (48) and a plurality of cover plates (86a) retained in the blade attachment slots (34) of a rotor disk (30). Each blade has a platform (46) with a trailing edge (58), and each cover plate includes at least one conduit (120, 126) for drawing leakage air from a plenum (102) in front of the disk and impinging that air against the platform trailing edges (58) to cool the tailing edges. In the preferred embodiment, each conduit (120) is defined by the rear face of a blade root (40) and a groove (122) cast into the cover plate. The invention makes productive use of leakage air by using that air to cool the platform trailing edges rather than allowing it to flow unbeneficially into the engine gaspath (24) in the vicinity of the platform leading edges (56).
摘要翻译： 用于燃气涡轮发动机的冷却转子组件包括转子叶片（48）和保持在转子盘（30）的叶片附接槽（34）中的多个盖板（86a）。 每个叶片具有具有后缘（58）的平台（46），并且每个盖板包括至少一个导管（120,126），用于从盘前面的压力室（102）吸取泄漏的空气，并使空气抵抗 平台后缘（58）以冷却后缘。 在优选实施例中，每个导管（120）由叶片根部（40）的后表面和浇注到盖板中的凹槽（122）限定。 本发明通过使用该空气来冷却平台后缘，而不是使其不受益地流动到平台前缘附近的发动机气路（24）中，从而有效利用泄漏空气。
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公开(公告)号：US10364680B2
公开(公告)日：2019-07-30
申请号：US13585274
申请日：2012-08-14
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.
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公开(公告)号：US09777582B2
公开(公告)日：2017-10-03
申请号：US14143115
申请日：2013-12-30
CPC分类号： F01D5/20 , F01D9/02 , F01D11/08 , F05D2220/32 , F05D2240/126 , Y02T50/673
摘要： An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control vane is formed with an outer surface of the tip wall and a winglet is formed at a junction between the suction sidewall and the tip leakage control vane.
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公开(公告)号：US09296039B2
公开(公告)日：2016-03-29
申请号：US13454197
申请日：2012-04-24
申请人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
发明人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
CPC分类号： B22C9/04 , B22C9/10 , B22C9/24 , B22F3/1017 , B22F3/105 , B22F3/1055 , B22F5/04 , B23K15/0086 , B33Y10/00 , B33Y80/00 , C21D9/0068 , F01D5/187 , F05D2240/303 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y02P10/292 , Y02P10/295
摘要： An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.
摘要翻译： 机翼具有主体，其包括通过间隔开的压力和吸力侧连接的前缘和后缘以提供外部翼面表面。 前缘壁在前缘提供外部翼型表面。 冲击壁与前缘壁一体地形成，以在前缘壁和冲击壁之间提供冲击腔，并且多个冲击孔设置在冲击壁中。 冲击孔横向穿过冲击壁间隔开。 一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积到彼此上，参考与翼型的特定横截面相关的CAD数据并将翼片相互连接，并产生翼型件。
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公开(公告)号：US09273560B2
公开(公告)日：2016-03-01
申请号：US13544274
申请日：2012-07-09
申请人： Matthew S. Gleiner , Mark F. Zelesky , Atul Kohli
发明人： Matthew S. Gleiner , Mark F. Zelesky , Atul Kohli
CPC分类号： F01D5/187 , F01D5/186 , F01D9/065 , F01D25/12 , F05D2240/81 , F05D2250/21 , F05D2250/232 , F05D2260/202 , F23R2900/03042 , Y02T50/676 , Y10T29/49234
摘要： A component for a gas turbine engine includes a wall and a cooling hole extending through the wall. The wall has a first surface and a second surface. The cooling hole includes a metering section extending downstream from an inlet in the first surface of the wall and a diffusion section extending from the metering section to an outlet in the second surface of the wall. The diffusion section includes a first plurality of lobes diverging longitudinally and laterally from the metering section on a first side of a centerline axis of the cooling hole and a second plurality of lobes diverging longitudinally and laterally from the metering section on a second side of the centerline axis.
摘要翻译： 用于燃气涡轮发动机的部件包括壁和延伸穿过壁的冷却孔。 该壁具有第一表面和第二表面。 冷却孔包括从壁的第一表面中的入口的下游延伸的计量部分和从计量部分延伸到壁的第二表面中的出口的扩散部分。 扩散部分包括在冷却孔的中心线轴线的第一侧上从计量部分纵向和横向分叉的第一多个凸角，以及在中心线的第二侧上从计量部分纵向和横向分叉的第二多个凸角 轴。
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