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11. 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。

12. 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。

13. 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。

14. 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。

15. 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。

16. 发明申请

US20150118057A1 MULTI-WALL GAS TURBINE AIRFOIL CAST USING A CERAMIC CORE FORMED WITH A FUGITIVE INSERT AND METHOD OF MANUFACTURING SAME 有权
标题翻译：多层气体涡轮机空气采用陶瓷铸造而成，具有易燃插件及其制造方法
公开(公告)号：US20150118057A1
公开(公告)日：2015-04-30
申请号：US14068061
申请日：2013-10-31
申请人： Ching-Pang Lee , Gary B. Merrill
发明人： Ching-Pang Lee , Gary B. Merrill
IPC分类号： F01D5/14 , B22C9/24 , B22C9/10
CPC分类号： B22C9/24 , B22C7/02 , B22C9/10 , B22C21/14 , F01D5/147 , F01D5/187 , F05D2230/211
摘要： A multi-wall gas turbine airfoil (192) and method of forming same using a casting core (150) having a monolithic body configured to define a pressure side wall (12), a suction side wall (14), and a third wall (16). The casting core is formed around a fugitive insert (96) during a single pour casting process.
摘要翻译：一种多壁燃气轮机翼型（192）及其使用具有整体式铸件（150）的成形方法，所述整体式主体构造成限定压力侧壁（12），吸力侧壁（14）和第三壁（ 16）。在单次浇铸过程期间，铸芯在短片（96）周围形成。

17. 发明授权

US09010125B2 Regeneratively cooled transition duct with transversely buffered impingement nozzles 有权
标题翻译：具有横向缓冲冲击喷嘴的再生冷却过渡管道
公开(公告)号：US09010125B2
公开(公告)日：2015-04-21
申请号：US13956405
申请日：2013-08-01
申请人： Jay A. Morrison , Ching-Pang Lee , Michael E. Crawford
发明人： Jay A. Morrison , Ching-Pang Lee , Michael E. Crawford
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F23R3/002 , F23R2900/03043 , F23R2900/03044
摘要： A cooling arrangement (56) having: a duct (30) configured to receive hot gases (16) from a combustor; and a flow sleeve (50) surrounding the duct and defining a cooling plenum (52) there between, wherein the flow sleeve is configured to form impingement cooling jets (70) emanating from dimples (82) in the flow sleeve effective to predominately cool the duct in an impingement cooling zone (60), and wherein the flow sleeve defines a convection cooling zone (64) effective to cool the duct solely via a cross-flow (76), the cross-flow comprising cooling fluid (72) exhausting from the impingement cooling zone. In the impingement cooling zone an undimpled portion (84) of the flow sleeve tapers away from the duct as the undimpled portion nears the convection cooling zone. The flow sleeve is configured to effect a greater velocity of the cross-flow in the convection cooling zone than in the impingement cooling zone.
摘要翻译：一种冷却装置（56），其具有：构造成从燃烧器接收热气体（16）的管道（30）以及围绕所述管道并且在其间限定冷却气室（52）的流动套管（50），其中所述流动套筒构造成形成从所述流动套筒中的凹坑（82）发出的冲击冷却喷嘴（70），其有效地主要地冷却（60）中的管道，并且其中所述流动套管限定有效地仅通过交叉流（76）来冷却所述管道的对流冷却区域（64），所述交叉流动包括冷却流体（72）从冲击冷却区。在冲击冷却区域中，随着未折射部分靠近对流冷却区，流动套管的未折弯部分（84）从导管逐渐变细。流动套筒构造成在对流冷却区域中产生比在冲击冷却区域更大的交叉流速度。

18. 发明授权

US08985949B2 Cooling system including wavy cooling chamber in a trailing edge portion of an airfoil assembly 有权
标题翻译：在翼型组件的后缘部分包括波浪冷却室的冷却系统
公开(公告)号：US08985949B2
公开(公告)日：2015-03-24
申请号：US13872229
申请日：2013-04-29
申请人： Ching-Pang Lee , Ralph W. Matthews , Gm Salam Azad , Manjit Shivanand
发明人： Ching-Pang Lee , Ralph W. Matthews , Gm Salam Azad , Manjit Shivanand
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/186 , F01D5/187 , F05D2240/304 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2250/294 , F05D2260/201 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141
摘要： An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.
摘要翻译：燃气涡轮发动机中的翼型件包括外壁，冷却流体腔和冷却系统。外壁具有前缘，后缘，压力侧，吸力侧以及径向内外端。冷却流体腔被限定在外壁中，大致径向延伸在外壁的内端和外端之间，并接收用于冷却外壁的冷却流体。冷却系统接收来自冷却流体腔的冷却流体，用于冷却外壁的后缘部分，并且包括由相对的第一和第二侧壁限定的冷却流体室，该第一和第二侧壁包括相应的交替成角度的部分，这些部分为冷却流体室提供Z字形。

19. 发明授权

US08936067B2 Casting core for a cooling arrangement for a gas turbine component 有权
标题翻译：用于燃气轮机部件的冷却装置的铸芯
公开(公告)号：US08936067B2
公开(公告)日：2015-01-20
申请号：US13658045
申请日：2012-10-23
申请人： Ching-Pang Lee , Benjamin E. Heneveld
发明人： Ching-Pang Lee , Benjamin E. Heneveld
IPC分类号： B22C9/10
CPC分类号： B22C9/10 , F01D5/186 , F01D5/187 , F05D2230/21 , F05D2230/211
摘要： A ceramic casting core, including: a plurality of rows (162, 166, 168) of gaps (164), each gap (164) defining an airfoil shape; interstitial core material (172) that defines and separates adjacent gaps (164) in each row (162, 166, 168); and connecting core material (178) that connects adjacent rows (170, 174, 176) of interstitial core material (172). Ends of interstitial core material (172) in one row (170, 174, 176) align with ends of interstitial core material (172) in an adjacent row (170, 174, 176) to form a plurality of continuous and serpentine shaped structures each including interstitial core material (172) from at least two adjacent rows (170, 174, 176) and connecting core material (178).
摘要翻译：一种陶瓷铸造芯，包括：多个间隔（164）的排（162,166,168），每个间隙（164）限定翼型形状; 间隙芯材料（172），其限定和分隔每排（162,166,168）中的相邻间隙（164）; 以及连接芯材料（178），其连接间隙芯材料（172）的相邻行（170,174,176）。一排（170,174,176）中的间隙芯材（172）的端部与相邻排（170,174,176）中的间隙芯材（172）的端部对准，以形成多个连续和蛇形形状的结构包括来自至少两个相邻行（170,174,176）和连接芯材（178）的间隙芯材料（172）。

20. 发明申请

US20150003973A1 AFT OUTER RIM SEAL ARRANGEMENT 有权
标题翻译： AFT外部RIM密封安排
公开(公告)号：US20150003973A1
公开(公告)日：2015-01-01
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
IPC分类号： F01D11/02 , F01D5/18
CPC分类号： F01D11/02 , F01D5/082 , F01D5/18 , F01D5/187 , F01D11/04 , F05D2260/14
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译：外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面（74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

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