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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：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：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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