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1. 发明授权

US06582834B2 Anti-stick coating for internal passages of turbine components 失效
公开(公告)号：US06582834B2
公开(公告)日：2003-06-24
申请号：US09879691
申请日：2001-06-12
申请人： Bangalore Aswatha Nagaraj , Ching-Pang Lee , William Randolph Stowell , Aaron Dennis Gastrich
发明人： Bangalore Aswatha Nagaraj , Ching-Pang Lee , William Randolph Stowell , Aaron Dennis Gastrich
IPC分类号： B32B1504
CPC分类号： C23C16/045 , C23C16/40 , C23C28/00 , F01D5/288 , F05D2230/90 , F05D2300/611 , Y10T428/12458 , Y10T428/12611 , Y10T428/12618 , Y10T428/12736 , Y10T428/12944 , Y10T428/24975 , Y10T428/265
摘要： An anti-stick coating that inhibits the adhesion of contaminants that form deposits on the internal cooling passages of gas turbine engine components. The anti-stick coating is formed as an outer coating of the internal cooling passages, and preferably overlies an environmental coating such as a diffusion aluminide coating formed on the passage surfaces. The outer coating has a thickness of not greater than three micrometers, and is resistant to adhesion by dirt contaminants as a result of comprising at least one layer of tantala, titania, hafnia, niobium oxide, yttria, silica and/or alumina. The outer coating is preferably deposited directly on the environmental coating by chemical vapor deposition.

2. 发明授权

US06933066B2 Thermal barrier coating protected by tantalum oxide and method for preparing same 失效
标题翻译：由氧化钽保护的热障涂层及其制备方法
公开(公告)号：US06933066B2
公开(公告)日：2005-08-23
申请号：US10317731
申请日：2002-12-12
申请人： Bangalore Aswatha Nagaraj , John Frederick Ackerman , William Randolph Stowell , Ching-Pang Lee
发明人： Bangalore Aswatha Nagaraj , John Frederick Ackerman , William Randolph Stowell , Ching-Pang Lee
IPC分类号： B32B3/00 , B32B15/04 , C23C16/06 , C23C28/00 , C23C30/00 , F03B3/12
CPC分类号： C23C28/00 , C23C30/00 , F01D5/288 , F05D2240/11 , F05D2300/21 , Y10T428/24917 , Y10T428/24926 , Y10T428/265
摘要： A thermal barrier coating for an underlying metal substrate of articles that operate at, or are exposed to, high temperatures, as well as being exposed to environmental contaminant compositions. This coating includes an inner layer nearest to the underlying metal substrate comprising a ceramic thermal barrier coating material, as well as an outer layer having an exposed surface and comprising tantalum oxide in an amount sufficient to protect the thermal barrier coating at least partially against environmental contaminants that become deposited on the exposed surface and optionally an intermediate layer between the inner and outer layers comprising alumina. This coating can be used to provide a thermally protected article having a metal substrate and optionally a bond coat layer adjacent to and overlaying the metal substrate. The thermal barrier coating can be prepared by forming the inner layer comprising the ceramic thermal barrier material, optionally forming the intermediate layer comprising the alumina over the inner layer, and then forming the outer layer comprising the tantalum oxide over the intermediate (inner) layer.
摘要翻译：用于在高温下操作或暴露于高温以及暴露于环境污染物组合物的制品的基础金属基底的热障涂层。该涂层包括最接近底层金属基底的内层，其包含陶瓷热障涂层材料，以及具有暴露表面的外层，并且包含足以保护热障涂层的氧化钽至少部分地防止环境污染物其沉积在暴露的表面上，并且任选地沉积在包含氧化铝的内层和外层之间的中间层。该涂层可用于提供具有金属基底和任选的与金属基底相邻并覆盖金属基底的粘合涂层的热保护制品。可以通过形成包含陶瓷热障材料的内层，任选地在内层上形成包含氧化铝的中间层，然后在中间（内）层上形成包含氧化钽的外层来制备热障涂层。

3. 发明授权

US07341427B2 Gas turbine nozzle segment and process therefor 有权
标题翻译：燃气轮机喷嘴段及其工艺
公开(公告)号：US07341427B2
公开(公告)日：2008-03-11
申请号：US11306221
申请日：2005-12-20
申请人： Andrew David Farmer , Bangalore Aswatha Nagaraj , Wenfeng Lu , Ching-Pang Lee , Joseph Michael Guentert
发明人： Andrew David Farmer , Bangalore Aswatha Nagaraj , Wenfeng Lu , Ching-Pang Lee , Joseph Michael Guentert
IPC分类号： F04D9/02
CPC分类号： F01D5/288 , F01D9/041 , F05D2220/31 , F05D2230/21 , F05D2230/31 , F05D2230/90 , F05D2260/95 , F05D2300/15 , F05D2300/611
摘要： A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.
摘要翻译：一种燃气涡轮发动机喷嘴段和用于生产这种喷嘴段的工艺，以显示出改善的耐久性和空气动力性能。该过程产生具有在一对平台之间并互连的至少一个叶片的喷嘴段。喷嘴段由伽马强化镍基超级合金铸造，其表面被热喷涂为由MCrAlX型涂层材料形成的环境涂层。然后对环境涂层的表面进行加工，使涂层的表面光洁度小于2.0微米。然后在喷嘴段中钻出冷却孔，然后在喷嘴段的平滑表面上施加耐氧化涂层，以便保持表面光洁度小于2.0微米Ra的喷嘴段上的最外表面。

4. 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.

5. 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。

6. 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。

7. 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。

8. 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。

9. 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。

10. 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。

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