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公开(公告)号：US09243500B2
公开(公告)日：2016-01-26
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：US20140047844A1
公开(公告)日：2014-02-20
申请号：US13585274
申请日：2012-08-14
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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公开(公告)号：US07097418B2
公开(公告)日：2006-08-29
申请号：US10870543
申请日：2004-06-18
申请人： Ricardo Trindade , Dan Que Pham , Larry Lebel
发明人： Ricardo Trindade , Dan Que Pham , Larry Lebel
IPC分类号： F03B11/02
CPC分类号： F01D9/041 , F01D5/18 , F05D2240/81
摘要： A gas turbine engine vane assembly provides double impingement cooling of a vane platform. An impingement structure disposed adjacent the vane platform defines at least first and second plenums in fluid flow communication, respectively defined in part by the vane platform. The vane platform has first and second surfaces defined within the first and second plenums, and which are cooled by successive impingement of secondary cooling air flow through the impingement structure.
摘要翻译： 燃气涡轮发动机叶片组件提供叶片平台的双重冲击冷却。 设置在叶片平台附近的冲击结构限定了至少分别由叶片平台限定的流体流动连通的第一和第二增压室。 叶片平台具有限定在第一和第二增压室内的第一和第二表面，并且通过次级冷却空气流连续冲击通过冲击结构而被冷却。
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公开(公告)号：US20060099073A1
公开(公告)日：2006-05-11
申请号：US10981466
申请日：2004-11-05
申请人： Toufik Djeridane , Timothy Blaskovich , Sri Sreekanth , Ricardo Trindade , Michael Clyde Papple , Olivier Bibor , Larry Lebel , Phillip Ligrani
发明人： Toufik Djeridane , Timothy Blaskovich , Sri Sreekanth , Ricardo Trindade , Michael Clyde Papple , Olivier Bibor , Larry Lebel , Phillip Ligrani
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2250/28 , F05D2250/61 , F05D2260/202 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F28F3/044 , F28F13/12
摘要： A dimple for use on a heat transfer surface exposed to a flowing gas, for use for example in a gas turbine engine, the dimple having an aspherical shape.
摘要翻译： 用于暴露于流动气体的传热表面的凹坑，用于例如在燃气涡轮发动机中，凹坑具有非球面形状。
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公开(公告)号：US09957801B2
公开(公告)日：2018-05-01
申请号：US13566400
申请日：2012-08-03
CPC分类号： F01D5/141 , F01D5/145 , F01D5/148 , F01D5/186 , F05D2240/124 , F05D2250/713
摘要： An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge.
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公开(公告)号：US20050135920A1
公开(公告)日：2005-06-23
申请号：US10736625
申请日：2003-12-17
申请人： Remy Synnott , Ricardo Trindade
发明人： Remy Synnott , Ricardo Trindade
CPC分类号： F01D25/14 , F01D9/041 , F05D2240/81 , F05D2260/203 , Y02T50/676
摘要： A vane assembly for a gas turbine engine comprises a plurality of airfoils extending between platforms and a plurality of effusion holes which are defined in at least one of the inner and outer platforms in a region intermediate adjacent airfoils. The effusion holes provide fluid flow communication between a cooling air source and the gas path.
摘要翻译： 用于燃气涡轮发动机的叶片组件包括在平台之间延伸的多个翼型件和在相邻翼型件之间的区域中限定在内平台和外平台中的至少一个中的多个排出孔。 渗出孔提供冷却空气源和气体通道之间的流体流动连通。
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7.发明授权公开(公告)号：US06406260B1
公开(公告)日：2002-06-18
申请号：US09425173
申请日：1999-10-22
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/127 , F05D2260/2212 , F05D2260/22141 , F28F3/04
摘要： A cooled airfoil has an internal cooling passage in which a plurality of trip strips are arranged to effect variable coolant flow and heat transfer coefficient distribution so as to advantageously minimize the amount of coolant flow required to adequately cool the airfoil structure. In one embodiment, this is accomplished by varying the dimensions of the trip strips along a transversal axis relative to the cooling passage.
摘要翻译： 冷却的翼型件具有内部冷却通道，其中布置多个跳闸带以实现可变的冷却剂流动和传热系数分布，以有利地最小化充分冷却翼型结构所需的冷却剂流量。 在一个实施例中，这是通过沿相对于冷却通道的横向轴线改变跳闸带的尺寸来实现的。
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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：US08105031B2
公开(公告)日：2012-01-31
申请号：US11971932
申请日：2008-01-10
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/185 , Y02T50/676
摘要： A turbine component includes an aft cooling circuit that extends between a turbine midsection and a turbine trailing end. The aft cooling circuit includes a trailing end section proximate the trailing end, a first interior section proximate the turbine midsection, and a first intermediate section fluidly connected between the trailing end section and the first interior section. A forward cooling circuit of the turbine component extends between the turbine midsection and a turbine leading end. The forward cooling circuit includes a leading end section proximate the leading end, a second interior section proximate the turbine midsection, and a plurality of second intermediate sections fluidly connected between the leading end section and the second interior section. The leading end section, the second intermediate section, the first intermediate section, and the trailing end section each include a plurality of coolant discharge openings for facilitating cooling of the turbine component.
摘要翻译： 涡轮机部件包括在涡轮机中部和涡轮机尾端之间延伸的后冷却回路。 后冷却回路包括靠近后端的后端部分，靠近涡轮机中部的第一内部部分和流体连接在后端部分和第一内部部分之间的第一中间部分。 涡轮机部件的向前冷却回路在涡轮机中部和涡轮机前端之间延伸。 前向冷却回路包括靠近前端的前端部分，靠近涡轮机中部的第二内部部分和流体连接在前端部分和第二内部部分之间的多个第二中间部分。 前端部分，第二中间部分，第一中间部分和后端部分均包括多个用于促进涡轮部件冷却的冷却剂排放口。
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公开(公告)号：US07901180B2
公开(公告)日：2011-03-08
申请号：US11800597
申请日：2007-05-07
申请人： William Abdel-Messeh , Andrew J. Lutz , Douglas E. Duke , Jose A. Lopes , Aaron T. Frost , Kevin J. Pallos , Kenneth J. Sawyer , Eric Herbst , Michael D. Greenberg , Ricardo Trindade
发明人： William Abdel-Messeh , Andrew J. Lutz , Douglas E. Duke , Jose A. Lopes , Aaron T. Frost , Kevin J. Pallos , Kenneth J. Sawyer , Eric Herbst , Michael D. Greenberg , Ricardo Trindade
CPC分类号： F01D5/187 , F01D5/225 , F05D2250/25 , F05D2260/2212 , Y10T29/49341
摘要： The ends of cooling air passages in turbine blades and/or vanes of a gas turbine engine are provided with turbulation promoters to enhance the cooling of such structures as inner and outer shrouds and the like to accommodate thermal loads thereon.
摘要翻译： 在涡轮机叶片和/或燃气涡轮发动机的叶片中的冷却空气通道的端部设置有湍流促进器，以增强诸如内部和外部护罩等的这种结构的冷却，以适应其上的热负荷。
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