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1. 发明授权

US09759072B2 Gas turbine engine airfoil cooling circuit arrangement 有权
公开(公告)号：US09759072B2
公开(公告)日：2017-09-12
申请号：US13599226
申请日：2012-08-30
申请人： Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
发明人： Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/188 , F01D5/187 , F01D5/189 , F01D9/041 , F01D25/12 , F02C7/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/126 , F05D2240/30 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure including, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.

2. 发明授权

US09222364B2 Platform cooling circuit for a gas turbine engine component 有权
标题翻译：用于燃气涡轮发动机部件的平台冷却回路
公开(公告)号：US09222364B2
公开(公告)日：2015-12-29
申请号：US13586110
申请日：2012-08-15
申请人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
发明人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
IPC分类号： F01D9/02 , F01D5/18
CPC分类号： F01D9/041 , F01D5/187 , F01D9/023 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/22141 , 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 having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.
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具有第一路径侧和第二路径侧的平台以及设置在第一路径侧和第二路径侧中的一个上的平台冷却回路平台的路径一侧。平台冷却回路包括第一芯腔，与第一芯腔流体连通的空腔，以及定位成覆盖至少空腔的盖板。

3. 发明申请

US20140047843A1 PLATFORM COOLING CIRCUIT FOR A GAS TURBINE ENGINE COMPONENT 有权
标题翻译：用于气体涡轮发动机部件的平台冷却回路
公开(公告)号：US20140047843A1
公开(公告)日：2014-02-20
申请号：US13586110
申请日：2012-08-15
申请人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
发明人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
IPC分类号： F02C7/18 , F01D25/12 , F02C3/04 , F01D9/02
CPC分类号： F01D9/041 , F01D5/187 , F01D9/023 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/22141 , 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 having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.
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具有第一路径侧和第二路径侧的平台以及设置在第一路径侧和第二路径侧中的一个上的平台冷却回路平台的路径一侧。平台冷却回路包括第一芯腔，与第一芯腔流体连通的空腔，以及定位成覆盖至少空腔的盖板。

4. 发明授权

US08961108B2 Cooling system for a turbine vane 有权
标题翻译：涡轮叶片冷却系统
公开(公告)号：US08961108B2
公开(公告)日：2015-02-24
申请号：US13439277
申请日：2012-04-04
申请人： Russell J. Bergman , Shawn J. Gregg , Michael Papple , Paul M. Lutjen , Joseph T. Caprario , Mohammed Ennacer , Thurman Carlo Dabbs
发明人： Russell J. Bergman , Shawn J. Gregg , Michael Papple , Paul M. Lutjen , Joseph T. Caprario , Mohammed Ennacer , Thurman Carlo Dabbs
IPC分类号： F01D9/06
CPC分类号： F01D25/246 , F01D25/14 , F05D2240/81
摘要： A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.
摘要翻译：用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。第一冷却流通道与第一集气室流体连通，并且在定子叶片的翼型内具有第一翼型冷却通道。第一翼型冷却通道用于冷却翼型件的前缘。第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。第一冷却流通道和第二冷却流通道设置在安装钩内。第一冷却流路和第二冷却流路不相互流体连通。

5. 发明申请

US20130266416A1 COOLING SYSTEM FOR A TURBINE VANE 有权
标题翻译：涡轮风扇冷却系统
公开(公告)号：US20130266416A1
公开(公告)日：2013-10-10
申请号：US13439277
申请日：2012-04-04
申请人： Russell J. Bergman , Shawn J. Gregg , Michael Papple , Paul M. Lutjen , Joseph T. Caprario , Mohammed Ennacer , Thurman Carlo Dabbs
发明人： Russell J. Bergman , Shawn J. Gregg , Michael Papple , Paul M. Lutjen , Joseph T. Caprario , Mohammed Ennacer , Thurman Carlo Dabbs
IPC分类号： F01D25/12 , F01D9/02
CPC分类号： F01D25/246 , F01D25/14 , F05D2240/81
摘要： A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.
摘要翻译：用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。第一冷却流通道与第一集气室流体连通，并且在定子叶片的翼型内具有第一翼型冷却通道。第一翼型冷却通道用于冷却翼型件的前缘。第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。第一冷却流通道和第二冷却流通道设置在安装钩内。第一冷却流路和第二冷却流路不相互流体连通。

6. 发明授权

US07467924B2 Turbine blade including revised platform 有权
标题翻译：涡轮叶片包括修订平台
公开(公告)号：US07467924B2
公开(公告)日：2008-12-23
申请号：US11205274
申请日：2005-08-16
申请人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
发明人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
IPC分类号： F01D5/10
CPC分类号： F01D5/3007 , F01D5/22 , F05D2230/31 , F05D2300/132
摘要： The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly from the airfoil and a root portion extending downwardly from the platform. Two suction side tabs extend a first distance outward from a suction side of the root potion. Two pressure side tabs extend outward from a pressure side of the root portion. One of the two pressure side tabs extends outward a distance similar to the first distance, however, the other of the two pressure side tabs extends outward a distance much smaller than the first distance, which reduces stresses acting on the turbine blade. In addition, a plurality of coatings are systematically applied to the turbine blade to further reduce mechanical stress factors and improve cooling.
摘要翻译：本发明提供一种涡轮叶片，其具有经修改的平台外结构，其包括独特的涂层组合，其减小涡轮叶片内的机械应力因素。涡轮叶片包括具有从翼型件向上延伸的翼型件和从该平台向下延伸的根部的平台。两个吸力侧翼片从根部的吸力侧向外延伸第一距离。两个压力侧翼片从根部的压力侧向外延伸。两个压力侧翼片之一向外延伸一段类似于第一距离的距离，然而，两个压力侧翼片中的另一个突出部向外延伸远远小于第一距离，这减小了作用在涡轮叶片上的应力。另外，将多个涂层系统地施加到涡轮叶片上，以进一步减少机械应力因素并改善冷却。

7. 发明授权

US07452186B2 Turbine blade including revised trailing edge cooling 有权
标题翻译：涡轮叶片包括修正后缘冷却
公开(公告)号：US07452186B2
公开(公告)日：2008-11-18
申请号：US11205299
申请日：2005-08-16
申请人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
发明人： Robert A. Charbonneau , Kenneth P. Botticello , Shawn J. Gregg , Kirk David Hlavaty , Jeffrey R. Levine , Kenneth A. Lonczak , Craig R. McGarrah , Dominic J. Mongillo , Lisa P. O'Neill , Edward Pietraszkiewicz , Richard M. Salzillo , Heather Ann Terry
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： The present invention provides an improved cooling circuit for a trailing edge of a turbine blade. The cooling circuit includes an inlet passage that receives a airflow and distributes the airflow through a feed passage. The feed passage primarily includes trip strips, at least one barrier including cross-over holes, teardrop shaped protrusions, and pockets disposed along a trailing edge. The geometry and positioning of both the cross-over holes and teardrop shaped protrusions downstream of the cross-over holes have been optimized to maximize cooling efficiency and reduce airflow. An improved transition between the inlet passage and the feed passage is also provided, which is arcuate and allows the airflow to maintain attachment and flow unimpeded from the inlet passage to the feed passage. The geometry of the pockets disposed along the trailing edge is optimized to improve cooling.
摘要翻译：本发明提供了一种用于涡轮叶片的后缘的改进的冷却回路。冷却回路包括入口通道，其接收气流并将气流分配通过进料通道。进料通道主要包括跳闸带，至少一个屏障，包括交叉孔，泪珠形突起和沿后缘设置的凹穴。交叉孔下游的交叉孔和泪滴形突起的几何形状和定位已被优化，以最大化冷却效率并减少气流。还提供了入口通道和进料通道之间的改进的过渡，其是弧形的并且允许气流保持附件和流动从入口通道畅通到进给通道。沿着后缘设置的凹穴的几何形状被优化以改善冷却。

8. 发明授权

US07059825B2 Cooled rotor blade 有权
标题翻译：冷却转子叶片
公开(公告)号：US07059825B2
公开(公告)日：2006-06-13
申请号：US10855149
申请日：2004-05-27
申请人： John W. Magowan , David Krause , Frank Thomas Cucinella , Raymond C. Surace , Shawn J. Gregg , Dominic J. Mongillo, Jr.
发明人： John W. Magowan , David Krause , Frank Thomas Cucinella , Raymond C. Surace , Shawn J. Gregg , Dominic J. Mongillo, Jr.
IPC分类号： F01D5/18
CPC分类号： F01D5/3007 , F01D5/081 , F01D5/187
摘要： A rotor blade is provided having a hollow airfoil with a cavity and an attached root. The root has a leading edge conduit, at least one mid-body conduit, and a trailing edge conduit. Each conduit has a centerline. The leading edge conduit includes an inlet having a forward side, a suction side, and a pressure side that diverge from the centerline of the leading edge conduit, and an aft side. Each of the mid-body conduits includes an inlet having a suction side and a pressure side that diverge from the centerline of the mid-body conduit, and an aft side and a forward side. The trailing edge conduit includes an inlet having a suction side and a pressure side that diverge from the centerline of the trailing edge conduit. The trailing edge conduit inlet further includes a forward side and an aft side.
摘要翻译：提供了一种转子叶片，其具有具有空腔和附接根部的中空翼型件。根具有前缘导管，至少一个中体导管和后缘导管。每个导管都有一个中心线。前缘导管包括具有从前缘导管的中心线和后侧分叉的前侧，吸力侧和压力侧的入口。每个中体导管包括具有吸入侧和从中体导管的中心线分叉的压力侧的入口，以及后侧和前侧。后缘导管包括具有从后缘导管的中心线分叉的吸入侧和压力侧的入口。后缘导管进口还包括前侧和后侧。

9. 发明授权

US07018176B2 Cooled turbine airfoil 有权
标题翻译：冷却涡轮机翼型
公开(公告)号：US07018176B2
公开(公告)日：2006-03-28
申请号：US10840546
申请日：2004-05-06
申请人： Dominic J. Mongillo , Shawn J. Gregg , Ruthann Mercadante
发明人： Dominic J. Mongillo , Shawn J. Gregg , Ruthann Mercadante
IPC分类号： F01D25/12
CPC分类号： F01D5/187 , F05D2250/70 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/22141
摘要： According to the present invention, a hollow airfoil is provided that comprises a leading edge wall portion, a plurality of cavities, one or more crossover ribs, a plurality of cooling apertures, and a plurality of impingement ribs. The cavities are disposed adjacent the leading edge wall portion, between the leading edge wall portion and a first rib. The crossover ribs extend between the leading edge wall portion and the first rib, and at least one crossover rib is disposed between a pair of the cavities. The cooling apertures are disposed in the leading edge wall portion, providing a passage through which cooling air can exit the cavities. The impingement apertures are disposed in the first rib, providing a passage through which cooling air can enter the cavities. At least one of the impingement apertures is contiguous with one of the crossover ribs.
摘要翻译：根据本发明，提供一种中空翼片，其包括前缘壁部分，多个空腔，一个或多个交叉肋，多个冷却孔和多个冲击肋。这些空腔邻近前缘壁部分设置在前缘壁部分和第一肋条之间。交叉肋在前缘壁部和第一肋之间延伸，并且至少一个交叉肋设置在一对空腔之间。冷却孔设置在前缘壁部分中，提供冷却空气可以通过该通道离开空腔的通道。冲击孔设置在第一肋中，提供冷却空气可以通过该通道进入空腔的通道。冲击孔中的至少一个与交叉肋中的一个相邻。

10. 发明授权

US07665968B2 Cooled rotor blade 有权
标题翻译：冷却转子叶片
公开(公告)号：US07665968B2
公开(公告)日：2010-02-23
申请号：US10855183
申请日：2004-05-27
申请人： Dominic J. Mongillo, Jr. , Shawn J. Gregg , Jeffrey R. Levine , Edward Pietraszkiewicz
发明人： Dominic J. Mongillo, Jr. , Shawn J. Gregg , Jeffrey R. Levine , Edward Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： A rotor blade is provided that includes a root and a hollow airfoil. The hollow airfoil has a cavity defined by a suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a passage disposed adjacent the leading edge, and an axially extending passage disposed adjacent the tip. The first passage is connected to the second passage. The second passage includes an opening disposed at the trailing edge of the airfoil. A conduit is disposed within the root that is operable to permit airflow through the root and into the leading edge passage, wherein the conduit provides the primary path into the leading edge passage.
摘要翻译：提供了包括根部和中空翼型件的转子叶片。中空翼片具有由吸力侧壁，压力侧壁，前缘，后缘，底座和尖端限定的空腔。内部通道构造设置在空腔内。该构造包括邻近前缘设置的通道和邻近尖端设置的轴向延伸通道。第一个通道连接到第二个通道。第二通道包括设置在翼型的后缘处的开口。管道设置在根部内，其可操作以允许气流通过根部并进入前缘通道，其中导管将主路径提供到前缘通道中。

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