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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：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：US10180067B2
公开(公告)日：2019-01-15
申请号：US13485588
申请日：2012-05-31
申请人： Jeffrey S. Beattie , Scott D. Lewis , Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Jeffrey Michael Jacques , Brandon M. Rapp
发明人： Jeffrey S. Beattie , Scott D. Lewis , Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Jeffrey Michael Jacques , Brandon M. Rapp
摘要： A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.
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公开(公告)号：US20140321961A1
公开(公告)日：2014-10-30
申请号：US13485588
申请日：2012-05-31
申请人： Jeffrey S. Beattie , Scott D. Lewis , Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Jeffrey Michael Jacques , Brandon M. Rapp
发明人： Jeffrey S. Beattie , Scott D. Lewis , Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Jeffrey Michael Jacques , Brandon M. Rapp
CPC分类号： F01D5/085 , F01D5/081 , F01D5/187 , F01D25/12 , F05D2240/81 , F05D2260/202 , F05D2260/203
摘要： A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.
摘要翻译： 燃气涡轮发动机部件包括护罩，U形通道，内部冷却空气通道和U形通道冷却孔。 护罩包括前表面，后表面，第一侧面和第二侧面。 U形通道设置在护罩的后表面。 气路面连接前面，后面，第一侧面和第二侧面。 冷却表面将前面，后面，第一侧面和与气体通路面相对的第二侧面连接起来。 内部冷却空气通道延伸穿过护罩。 U通道冷却孔延伸到与U形槽相邻的护罩的第一侧面，以与内部冷却通道相交。
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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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