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公开(公告)号：WO2014004001A1
公开(公告)日：2014-01-03
申请号：PCT/US2013/044252
申请日：2013-06-05
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：WO2014051688A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/031368
申请日：2013-03-14
CPC分类号： F01D11/006 , F01D5/22 , F01D5/26 , F01D11/008
摘要： A seal damper system includes a plurality of circumferentially spaced blades that each include a platform and an airfoil that extends radially outwardly from the platform. A pocket is arranged circumferentially intermediate the blades and radially inwardly of the platform. A seal damper is arranged in the pocket. The seal damper includes a base section that extends along an axial dimension from a first axial end to an opposing second axial end. The base section joins a first arm that extends radially inwardly from the first axial end and a second arm that extends radially inwardly from the second axial end. The first arm includes a free end having a pair of spaced apart shoulders.
摘要翻译： 密封阻尼器系统包括多个周向间隔开的叶片，每个叶片包括平台和从平台径向向外延伸的翼型件。 一个口袋沿圆周方向布置在叶片和平台的径向内侧。 密封阻尼器布置在口袋中。 密封阻尼器包括基部，该基部沿轴向尺寸从第一轴向端延伸到相对的第二轴向端。 基部接合从第一轴向端径向向内延伸的第一臂和从第二轴向端径向向内延伸的第二臂。 第一臂包括具有一对间隔开的肩部的自由端。
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公开(公告)号：WO2015038605A1
公开(公告)日：2015-03-19
申请号：PCT/US2014/054940
申请日：2014-09-10
CPC分类号： F01D5/082 , F01D5/081 , F01D5/12 , F01D5/3007 , F01D5/3015 , F01D11/006 , F05D2220/32 , F05D2260/232
摘要： A turbine section comprises a rotor, blade and rim seal. The rotor comprises a rim defining an outer diameter surface, and a slot in the outer diameter surface. The blade comprises an airfoil, a platform surrounding the airfoil, a shank extending from the platform, a root extending from the shank for connecting to the slot, and a nub extending from the shank beneath the platform. The rim seal is disposed between the outer diameter surface and the nub. A method for cooling an outer diameter of a rotor disk comprises bleeding cooling air in a gas turbine engine, passing the flow of cooling air through a cover plate that retains a seal plate against the rotor disk, leaking the cooing air between a rotor disk rim and the seal plate, and guiding the cooling air across an outer diameter surface of the rotor disk rim utilizing a rim seal.
摘要翻译： 涡轮机部分包括转子，叶片和轮缘密封件。 转子包括限定外径表面的边缘和外径表面中的狭槽。 叶片包括翼型件，围绕翼型的平台，从平台延伸的柄，从柄延伸的用于连接到狭槽的根部，以及从平台下方的柄延伸的突出部。 边缘密封件设置在外径表面和凸起之间。 用于冷却转子盘的外径的方法包括使燃气涡轮发动机中的冷却空气渗出，使冷却空气流通过将密封板保持在转子盘上的盖板，使冷凝空气在转子盘轮圈 和密封板，并且利用边缘密封件将冷却空气引导到转子盘边缘的外径表面。
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公开(公告)号：WO2014003958A1
公开(公告)日：2014-01-03
申请号：PCT/US2013/043340
申请日：2013-05-30
发明人： ZELESKY, Mark, F. , TRINDADE, Ricardo , TELLER, Bret, M. , LEWIS, Scott, D. , BEATTIE, Jeffrey, S. , JACQUES, Jeffrey, Michael , RAPP, Brandon, M.
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： 一种用于燃气涡轮发动机的涡轮叶片包括一个翼型件，其包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供沿径向方向延伸的外部翼面。 后缘布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沿径向方向延伸到翼型件。 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：WO2015069362A2
公开(公告)日：2015-05-14
申请号：PCT/US2014/052032
申请日：2014-08-21
CPC分类号： F01D11/006 , F01D5/22 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/75 , F05D2260/22141
摘要： A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.
摘要翻译： 燃气涡轮发动机包括涡轮部分。 涡轮机部分包括可围绕轴线旋转的盘。 多个涡轮叶片安装在盘的周边周围，并且多个密封件布置在涡轮叶片和盘的周边之间。 每个密封件相对于轴线包括径向外表面和径向内表面。 径向内表面包括多个突起。
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6.发明申请
公开(公告)号：WO2013180792A2
公开(公告)日：2013-12-05
申请号：PCT/US2013/030332
申请日：2013-03-12
申请人： UNITED TECHNOLOGIES CORPORATION , LEVINE, Jeffrey, R. , BEATTIE, Jeffrey, S. , STADDON, Malcolm, C.
CPC分类号： F01D5/188 , B22C9/103 , B22C9/108 , F01D5/187 , F05D2200/33 , F05D2230/211 , F05D2260/22141 , F05D2260/607 , F05D2300/13 , Y02E10/721
摘要： An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip. A trailing edge cooling passage interconnects the cooling passage to the trailing edge. The trailing edge cooling passage includes first and second pedestals of different sizes that are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes.
摘要翻译： 机翼具有主体，其包括邻接压力侧和吸力侧的前缘和后缘，以提供外部翼型表面。 冷却通道在径向方向上从根部延伸到尖端。 后缘冷却通道将冷却通道与后缘相互连接。 后缘冷却通道包括不同尺寸的第一和第二基座，其相对于具有相同尺寸的基座并且相对于不同尺寸的基座以重复图案布置。
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