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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：US20130323078A1
公开(公告)日：2013-12-05
申请号：US13484767
申请日：2012-05-31
CPC分类号： F01D5/187 , B22C9/04 , B22C9/103 , F05D2230/211 , F05D2260/204 , Y02T50/676 , Y10T29/49316
摘要： A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.
摘要翻译： 一种制造翼型的方法包括以下步骤：制造第一芯，其包括限定完成的翼型件的第一多个通道的第一多个肋，并且制造为第二芯，该第二芯包括限定第二多个通路的第二多个肋 完成机翼。 第二多个肋包括多个支座。 所述多个支座在所述第一多个肋与所述第二多个肋之间设置间隔，以限定所述第一多个通道与所述完整翼型的所述第二多个通道之间的间隔。 然后将翼型件围绕芯组件成型。 一旦完成，移除芯组件以提供具有期望的稳定性和结构完整性的并入多个微电路的完整翼型件。
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公开(公告)号：US20140003950A1
公开(公告)日：2014-01-02
申请号：US13537127
申请日：2012-06-29
CPC分类号： F01D5/22 , F01D11/006 , F05D2230/64 , F05D2260/30 , Y10T29/49316
摘要： A method of assembling a blade array includes the step of inserting a blade having a platform into a rotor. The blade includes a pocket radially beneath the platform that includes an interference feature. The blade corresponds to one of first and second blades that are scaled versions of one another. The method includes the step of selecting a damper seal, and inserting the damper seal into the pocket. The damper seal corresponds to one of first and second damper seals. The first damper seal cooperates with the interference feature thereby permitting the first damper seal to fully seat within the pocket. The second damper seal is obstructed by the interference feature thereby preventing the second damper seal from fully seating within the pocket.
摘要翻译： 组装叶片阵列的方法包括将具有平台的叶片插入转子的步骤。 刀片包括径向在平台下方的口袋，其包括干涉特征。 叶片对应于第一和第二叶片之一，其是彼此缩放的版本。 该方法包括选择阻尼器密封件并将阻尼器密封件插入袋中的步骤。 阻尼器密封件对应于第一和第二阻尼器密封件之一。 第一阻尼器密封件与干涉特征协调，从而允许第一阻尼器密封件完全位于口袋内。 第二阻尼器密封件受到干涉特征的阻碍，从而防止第二阻尼器密封件完全位于口袋内。
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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：US09587495B2
公开(公告)日：2017-03-07
申请号：US13537127
申请日：2012-06-29
CPC分类号： F01D5/22 , F01D11/006 , F05D2230/64 , F05D2260/30 , Y10T29/49316
摘要： A method of assembling a blade array includes the step of inserting a blade having a platform into a rotor. The blade includes a pocket radially beneath the platform that includes an interference feature. The blade corresponds to one of first and second blades that are scaled versions of one another. The method includes the step of selecting a damper seal, and inserting the damper seal into the pocket. The damper seal corresponds to one of first and second damper seals. The first damper seal cooperates with the interference feature thereby permitting the first damper seal to fully seat within the pocket. The second damper seal is obstructed by the interference feature thereby preventing the second damper seal from fully seating within the pocket.
摘要翻译： 组装叶片阵列的方法包括将具有平台的叶片插入转子的步骤。 刀片包括径向在平台下方的口袋，其包括干涉特征。 叶片对应于第一和第二叶片之一，其是彼此缩放的版本。 该方法包括选择阻尼器密封件并将阻尼器密封件插入袋中的步骤。 阻尼器密封件对应于第一和第二阻尼器密封件之一。 第一阻尼器密封件与干涉特征协调，从而允许第一阻尼器密封件完全位于口袋内。 第二阻尼器密封件受到干涉特征的阻碍，从而防止第二阻尼器密封件完全位于口袋内。
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公开(公告)号：US09422817B2
公开(公告)日：2016-08-23
申请号：US13484767
申请日：2012-05-31
CPC分类号： F01D5/187 , B22C9/04 , B22C9/103 , F05D2230/211 , F05D2260/204 , Y02T50/676 , Y10T29/49316
摘要： A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.
摘要翻译： 一种制造翼型的方法包括以下步骤：制造第一芯，其包括限定完成的翼型件的第一多个通道的第一多个肋，并且制造为第二芯，该第二芯包括限定第二多个通路的第二多个肋 完成机翼。 第二多个肋包括多个支座。 所述多个支座在所述第一多个肋与所述第二多个肋之间设置间隔，以限定所述第一多个通道与所述完整翼型的所述第二多个通道之间的间隔。 然后将翼型件围绕芯组件成型。 一旦完成，移除芯组件以提供具有期望的稳定性和结构完整性的并入多个微电路的完整翼型件。
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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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