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1. 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。

2. 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。

3. 发明授权

US07186082B2 Cooled rotor blade and method for cooling a rotor blade 有权
标题翻译：冷却转子叶片和冷却转子叶片的方法
公开(公告)号：US07186082B2
公开(公告)日：2007-03-06
申请号：US10855010
申请日：2004-05-27
申请人： Dominic J. Mongillo, Jr. , Shawn J. Gregg
发明人： Dominic J. Mongillo, Jr. , Shawn J. Gregg
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/221 , F05D2260/22141
摘要： A rotor blade and a method for cooling a rotor blade are provided. The rotor blade includes a root and a hollow airfoil having a cavity defined by 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 serpentine passage having at least three radial segments connected to one another, an axially extending passage disposed between the tip and the serpentine passage, at least one aperture extending between the last radial segment and the axially extending passage, and one or more sink apertures disposed within one of the suction side wall or the pressure side wall of the last radial segment of the serpentine passage. At least one conduit is disposed within the root. The conduit is operable to permit airflow through the root and into the internal passage configuration.
摘要翻译：提供了一种用于冷却转子叶片的转子叶片和方法。转子叶片包括根部和具有由吸力侧壁，压力侧壁，前缘，后缘，基部和尖端限定的空腔的中空翼型件。内部通道构造设置在空腔内。该构造包括具有至少三个彼此连接的径向段的蛇形通道，设置在尖端和蛇形通道之间的轴向延伸的通道，在最后的径向段和轴向延伸通道之间延伸的至少一个孔，以及一个或多个设置在蛇形通道的最后一个径向段的吸入侧壁或压力侧壁之一内的吸入孔。至少一根导管设置在根部内。管道可操作以允许气流通过根部并进入内部通道构造。

4. 发明授权

US06929451B2 Cooled rotor blade with vibration damping device 有权
标题翻译：具有减振装置的冷却转子叶片
公开(公告)号：US06929451B2
公开(公告)日：2005-08-16
申请号：US10741106
申请日：2003-12-19
申请人： Shawn J. Gregg , Dominic J. Mongillo, Jr.
发明人： Shawn J. Gregg , Dominic J. Mongillo, Jr.
IPC分类号： F01D5/16 , F01D5/18 , F01D5/10
CPC分类号： F01D5/187 , F01D5/16 , F01D5/189 , F01D5/26 , F05D2240/126 , F05D2240/307 , F05D2260/22141 , Y10S416/50
摘要： A rotor blade for a rotor assembly is provided that includes a root, an airfoil, and a damper. The airfoil includes a base, a tip, a pressure side wall, a suction side wall, and a cavity disposed therebetween. The cavity extends substantially between the base and the tip, and includes a first cavity portion, a second cavity portion, and a channel disposed between the first cavity portion and the second cavity portion. A plurality of first pedestals are disposed within the first cavity portion adjacent the channel, and a plurality of second pedestals are disposed within the second cavity portion adjacent the channel. The damper is selectively received within the channel.
摘要翻译：提供了一种用于转子组件的转子叶片，其包括根部，翼型件和阻尼器。翼型件包括基座，尖端，压力侧壁，吸力侧壁和设置在其间的空腔。空腔基本上在基部和尖端之间延伸，并且包括第一空腔部分，第二空腔部分和设置在第一空腔部分和第二空腔部分之间的通道。多个第一基座设置在与通道相邻的第一空腔部分内，并且多个第二基座设置在邻近通道的第二空腔部分内。阻尼器选择性地接收在通道内。

5. 发明授权

US07125225B2 Cooled rotor blade with vibration damping device 有权
标题翻译：具有减振装置的冷却转子叶片
公开(公告)号：US07125225B2
公开(公告)日：2006-10-24
申请号：US10771587
申请日：2004-02-04
申请人： Raymond C. Surace , Edwin Otero , Shawn J. Gregg , Tracy A. Propheter
发明人： Raymond C. Surace , Edwin Otero , Shawn J. Gregg , Tracy A. Propheter
IPC分类号： F01D5/16
CPC分类号： F01D5/16 , F01D5/187 , F05D2250/71 , Y10S416/50
摘要： A rotor blade for a rotor assembly is provided that includes a root, an airfoil, and a damper. The airfoil has a length, a base, a tip, a first side wall, a second side wall, and at least one cavity. The length extends the base and the tip. The at least one cavity is disposed between the side walls, and the channel is defined by a first wall portion and a second wall portion. The damper, which is selectively received within the channel, includes a first bearing surface, a second bearing surface, a forward surface, and an aft surface, all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage within the channel. The passage has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper has an arcuate lengthwise extending centerline.
摘要翻译：提供了一种用于转子组件的转子叶片，其包括根部，翼型件和阻尼器。翼型件具有长度，底座，尖端，第一侧壁，第二侧壁和至少一个空腔。长度延长基部和尖端。所述至少一个空腔设置在所述侧壁之间，并且所述通道由第一壁部分和第二壁部分限定。选择性地容纳在通道内的阻尼器包括第一支承表面，第二支承表面，前表面和后表面，所有这些都沿纵向延伸。至少一个表面被成形为在通道内形成纵向延伸的通道。通道具有沿着至少一个表面的长度方向定向的流动方向，以允许冷却空气沿长度方向沿着至少一个表面行进。根据本发明的一个方面，阻尼器具有弓形的纵向延伸的中心线。

6. 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。

7. 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。

8. 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。

9. 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。

10. 发明授权

US08480366B2 Recessed metering standoffs for airfoil baffle 有权
标题翻译：翼形挡板的嵌入式计量支座
公开(公告)号：US08480366B2
公开(公告)日：2013-07-09
申请号：US13272784
申请日：2011-10-13
申请人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
发明人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/70 , F05D2260/202
摘要： An internally cooled airfoil comprises an airfoil body, a baffle and a plurality of standoffs. The airfoil body is shaped to form leading and trailing edges, and pressure and suction sides surrounding an internal cooling channel. The baffle is disposed within the internal cooling channel and comprises a liner body having a perimeter shaped to correspond to the shape of the internal cooling channel and to form a cooling air supply duct. The baffle includes a plurality of cooling holes extending through the liner body to direct cooling air from the supply duct into the internal cooling channel. The standoffs are recessed into a surface of either the baffle or the airfoil body such that a height of the standoffs is greater than the spacing.
摘要翻译：内部冷却的翼型件包括翼型本体，挡板和多个支座。翼型体成形为形成前缘和后缘，围绕内部冷却通道的压力和吸力侧。挡板设置在内部冷却通道内，并且包括衬套主体，其具有成形为对应于内部冷却通道的形状的周边并且形成冷却空气供应管道。挡板包括多个冷却孔，其延伸穿过衬套主体，以将冷却空气从供应管道引导到内部冷却通道中。支座凹入到挡板或翼型体的表面中，使得支座的高度大于间隔。

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