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1. 发明申请

US20120057968A1 RING SEGMENT WITH SERPENTINE COOLING PASSAGES 有权
标题翻译：带有SERPENTINE冷却通道的环形分段
公开(公告)号：US20120057968A1
公开(公告)日：2012-03-08
申请号：US13213417
申请日：2011-08-19
申请人： Ching-Pang Lee , Eric C. Berrong
发明人： Ching-Pang Lee , Eric C. Berrong
IPC分类号： F01D25/14
CPC分类号： F01D11/08 , F05D2250/70 , F05D2260/20
摘要： A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system receives cooling fluid from an outer side of the panel for cooling the panel and includes at least one cooling fluid supply passage, at least one serpentine cooling passage, and at least one cooling fluid discharge passage. The cooling fluid supply passage(s) receive the cooling fluid from the outer side of the panel and deliver the cooling fluid to a first cooling fluid chamber within the panel. The serpentine cooling passage(s) receive the cooling fluid from the first cooling fluid chamber, wherein the cooling fluid provides convective cooling to the panel as it passes through the serpentine cooling passage(s). The cooling fluid discharge passage(s) discharge the cooling fluid from the cooling system.
摘要翻译：用于燃气涡轮发动机的环段包括面板和冷却系统。冷却系统从面板的外侧接收冷却流体，用于冷却面板，并且包括至少一个冷却流体供应通道，至少一个蛇形冷却通道和至少一个冷却流体排出通道。冷却流体供应通道从面板的外侧接收冷却流体，并将冷却流体输送到面板内的第一冷却流体室。蛇形冷却通道从第一冷却流体室接收冷却流体，其中冷却流体在通过蛇形冷却通道时向面板提供对流冷却。冷却流体排出通道从冷却系统排出冷却流体。

2. 发明授权

US08727704B2 Ring segment with serpentine cooling passages 有权
标题翻译：带有蛇形冷却通道的环段
公开(公告)号：US08727704B2
公开(公告)日：2014-05-20
申请号：US13213417
申请日：2011-08-19
申请人： Ching-Pang Lee , Eric C. Berrong
发明人： Ching-Pang Lee , Eric C. Berrong
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F05D2250/70 , F05D2260/20
摘要： A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system receives cooling fluid from an outer side of the panel for cooling the panel and includes at least one cooling fluid supply passage, at least one serpentine cooling passage, and at least one cooling fluid discharge passage. The cooling fluid supply passage(s) receive the cooling fluid from the outer side of the panel and deliver the cooling fluid to a first cooling fluid chamber within the panel. The serpentine cooling passage(s) receive the cooling fluid from the first cooling fluid chamber, wherein the cooling fluid provides convective cooling to the panel as it passes through the serpentine cooling passage(s). The cooling fluid discharge passage(s) discharge the cooling fluid from the cooling system.
摘要翻译：用于燃气涡轮发动机的环段包括面板和冷却系统。冷却系统从面板的外侧接收冷却流体，用于冷却面板，并且包括至少一个冷却流体供应通道，至少一个蛇形冷却通道和至少一个冷却流体排出通道。冷却流体供应通道从面板的外侧接收冷却流体，并将冷却流体输送到面板内的第一冷却流体室。蛇形冷却通道从第一冷却流体室接收冷却流体，其中冷却流体在通过蛇形冷却通道时向面板提供对流冷却。冷却流体排出通道从冷却系统排出冷却流体。

3. 发明申请

US20120057960A1 RING SEGMENT WITH FORKED COOLING PASSAGES 有权
标题翻译：带有冷却通道的环形分段
公开(公告)号：US20120057960A1
公开(公告)日：2012-03-08
申请号：US13213459
申请日：2011-08-19
申请人： Eric C. Berrong , Ching-Pang Lee , Akash Bhatia , Ryan S. Yamane , Stefan Tschirren , Leonard J. Meyer
发明人： Eric C. Berrong , Ching-Pang Lee , Akash Bhatia , Ryan S. Yamane , Stefan Tschirren , Leonard J. Meyer
IPC分类号： F01D9/02
CPC分类号： F01D11/08 , F05D2250/70 , F05D2260/20
摘要： A ring segment is provided for a gas turbine engine includes a panel and a cooling system. Cooling fluid is provided to an outer side of the panel and an inner side of the panel defines at least a portion of a hot gas flow path through the engine. The cooling system is located within that panel and receives cooling fluid from the outer side of the panel for cooling the panel. The cooling system includes a plurality of cooling fluid passages that receive cooling fluid from the outer side of the panel. The cooling fluid passages each have a generally axially extending portion that includes at least one fork. The fork(s) divide each cooling fluid passage into at least two downstream portions that each receives cooling fluid from the respective axially extending portion.
摘要翻译：提供了一种用于燃气涡轮发动机的环段，其包括面板和冷却系统。冷却流体设置在面板的外侧，并且面板的内侧限定通过发动机的热气体流路的至少一部分。冷却系统位于该面板内并从面板的外侧接收冷却流体以冷却面板。冷却系统包括从板的外侧接收冷却流体的多个冷却流体通道。冷却流体通道各自具有包括至少一个叉的大致轴向延伸的部分。叉子将每个冷却流体通道分成至少两个下游部分，每个下游部分从相应的轴向延伸部分接收冷却流体。

4. 发明授权

US08894352B2 Ring segment with forked cooling passages 有权
标题翻译：带分叉冷却通道的环段
公开(公告)号：US08894352B2
公开(公告)日：2014-11-25
申请号：US13213459
申请日：2011-08-19
申请人： Eric C. Berrong , Ching-Pang Lee , Akash Bhatia , Ryan S. Yamane , Stefan Tschirren , Leonard J. Meyer
发明人： Eric C. Berrong , Ching-Pang Lee , Akash Bhatia , Ryan S. Yamane , Stefan Tschirren , Leonard J. Meyer
IPC分类号： F01D25/08 , F01D11/08
CPC分类号： F01D11/08 , F05D2250/70 , F05D2260/20
摘要： A ring segment is provided for a gas turbine engine includes a panel and a cooling system. Cooling fluid is provided to an outer side of the panel and an inner side of the panel defines at least a portion of a hot gas flow path through the engine. The cooling system is located within that panel and receives cooling fluid from the outer side of the panel for cooling the panel. The cooling system includes a plurality of cooling fluid passages that receive cooling fluid from the outer side of the panel. The cooling fluid passages each have a generally axially extending portion that includes at least one fork. The fork(s) divide each cooling fluid passage into at least two downstream portions that each receives cooling fluid from the respective axially extending portion.
摘要翻译：提供了一种用于燃气涡轮发动机的环段，其包括面板和冷却系统。冷却流体设置在面板的外侧，并且面板的内侧限定通过发动机的热气体流路的至少一部分。冷却系统位于该面板内并从面板的外侧接收冷却流体以冷却面板。冷却系统包括从板的外侧接收冷却流体的多个冷却流体通道。冷却流体通道各自具有包括至少一个叉的大致轴向延伸的部分。叉子将每个冷却流体通道分成至少两个下游部分，每个下游部分从相应的轴向延伸部分接收冷却流体。

5. 发明授权

US09630277B2 Airfoil having built-up surface with embedded cooling passage 有权
公开(公告)号：US09630277B2
公开(公告)日：2017-04-25
申请号：US12723880
申请日：2010-03-15
申请人： Ching-Pang Lee , Mrinal Munshi , Gm S. Azad , Jae Y. Um
发明人： Ching-Pang Lee , Mrinal Munshi , Gm S. Azad , Jae Y. Um
IPC分类号： F02C7/12 , B23P6/00 , F01D5/00 , F01D5/14 , F01D5/18
CPC分类号： B23P6/007 , F01D5/005 , F01D5/145 , F01D5/186 , F05D2230/30 , F05D2230/80 , F05D2240/81 , Y10T29/49318
摘要： A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.

6. 发明授权

US09347324B2 Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles 有权
标题翻译：具有冲击插入件的涡轮机翼型叶片具有多个冲击喷嘴
公开(公告)号：US09347324B2
公开(公告)日：2016-05-24
申请号：US14133773
申请日：2013-12-19
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/188 , F01D9/04 , F05D2210/33 , F05D2240/12 , F05D2240/127 , F05D2260/2212
摘要： A turbine vane includes a generally elongated hollow airfoil and a cooling system. The cooling system is positioned within the airfoil and includes a cooling chamber and an impingement insert positioned in the cooling chamber. The impingement insert and an inner surface of an outer wall of the airfoil define a cooling channel therebetween. The impingement insert includes a plurality of impingement nozzles extending toward the inner surface of the outer wall and a plurality of impingement orifices. At least one of the impingement orifices is arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the at least one impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice.
摘要翻译：涡轮叶片包括大致细长的中空翼型件和冷却系统。冷却系统定位在翼型内，并且包括冷却室和位于冷却室中的冲击插入件。冲击插入件和翼型件的外壁的内表面在它们之间限定冷却通道。冲击插入件包括朝向外壁的内表面延伸的多个冲击喷嘴和多个冲击孔。冲击孔中的至少一个相对于至少一个相邻的冲击孔布置成非对准图案，使得流出至少一个冲击孔的冷却流体不直接流入冷却流体流动路径的中心线从至少一个相邻的冲击孔流出的冷却流体。

7. 发明授权

US09206904B2 Seal including flexible seal strips 有权
标题翻译：密封包括柔性密封条
公开(公告)号：US09206904B2
公开(公告)日：2015-12-08
申请号：US12832141
申请日：2010-07-08
申请人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
发明人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
IPC分类号： F16J15/32 , F01D11/02
CPC分类号： F16J15/3292 , F01D11/02 , F05D2240/57
摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.
摘要翻译：一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。密封构件包括多个柔性密封条。每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的轴。密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

8. 发明授权

US09133721B2 Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine 有权
标题翻译：涡轮转换部件由用于燃气涡轮发动机的两段风冷多层外板形成
公开(公告)号：US09133721B2
公开(公告)日：2015-09-15
申请号：US12945948
申请日：2010-11-15
申请人： Ching-Pang Lee , Jay A. Morrison
发明人： Ching-Pang Lee , Jay A. Morrison
IPC分类号： F23R3/46 , F01D9/02 , F01D25/12
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译：公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室形成在内板和中间板之间。过渡管还可以包括外板。内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。

9. 发明授权

US09121298B2 Finned seal assembly for gas turbine engines 有权
标题翻译：燃气涡轮发动机的翅片密封组件
公开(公告)号：US09121298B2
公开(公告)日：2015-09-01
申请号：US13534060
申请日：2012-06-27
申请人： Ching-Pang Lee , Kok-Mun Tham , John M. Owen , Gary D. Lock , Carl M. Sangan , Vincent P. Laurello
发明人： Ching-Pang Lee , Kok-Mun Tham , John M. Owen , Gary D. Lock , Carl M. Sangan , Vincent P. Laurello
IPC分类号： F04D11/00 , F01D11/00
CPC分类号： F01D11/001
摘要： A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.
摘要翻译：设置在涡轮发动机中的热气体路径和盘腔之间的密封组件包括从转子结构的轴向相对侧朝向相邻的非旋转叶片组件延伸的环形外翼构件，以及径向向内延伸的多个翅片从外翼构件延伸并且朝向相邻的非旋转叶片组件延伸。翅片被布置成使得在相邻翅片之间限定具有圆周方向的部件的空间。在发动机操作期间，翅片的旋转使得吹扫空气从盘腔朝向热气体路径泵送，以通过迫使热的工作气体远离热空气路径来帮助限制热的工作气体从热气体路径泄漏到盘腔中密封组装。

10. 发明授权

US09028207B2 Cooled component wall in a turbine engine 有权
标题翻译：在涡轮发动机中冷却的部件壁
公开(公告)号：US09028207B2
公开(公告)日：2015-05-12
申请号：US12888467
申请日：2010-09-23
申请人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
发明人： Humberto A. Zuniga , Ching-Pang Lee , Michael E. Crawford
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2230/90 , F05D2250/13 , F05D2250/324 , Y10T29/4935
摘要： A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion.
摘要翻译：涡轮发动机中的部件壁包括基板，扩散部分和至少一个冷却通道。扩散部分位于衬底的表面中并且由第一侧壁和第二侧壁限定。冷却通道包括出口部分，冷却空气通过该出口部分朝向第一侧壁的方向流出。出口部分包括后部，前部和具有近端和远端的内壁。后部位于第一和第二侧壁之间。前部分在第一侧壁和内壁的远端之间延伸。第一侧壁延伸到冷却通道的出口部分到内壁，并从第一侧壁延伸到第二侧壁，以阻挡出口部分的前部。

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