公开(公告)号：US08926267B2

公开(公告)日：2015-01-06

申请号：US13766909

申请日：2013-02-14

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, Jr. ,  John J. Marra

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, Jr. ,  John J. Marra

IPC分类号： F01D25/12 ,  F01D5/14 ,  F01D9/06 ,  F02C7/12 ,  F01D5/18 ,  F01D5/08 ,  F01D11/00

CPC分类号： F01D5/187 ,  F01D5/082 ,  F01D5/143 ,  F01D9/065 ,  F01D11/001 ,  F01D25/12 ,  F02C7/12 ,  F05D2240/127

摘要： A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.

摘要翻译： 一种燃气涡轮发动机，包括：环境空气冷却回路（10），其具有设置在涡轮机叶片（22）中并与环境空气源（12）流体连通的冷却通道（26）;以及预旋流器 18），所述预旋转器具有：内罩（38）; 外护罩（56）; 以及多个导向叶片（42），每个导向叶片从内护罩跨越到外护罩。 周向相邻的导向叶片（46,48）在其间限定相应的喷嘴（44）。 通过涡轮叶片的旋转产生的力通过冷却回路激励环境空气。 预旋流器被配置为对通过喷嘴抽吸的环境空气赋予涡流，并且将旋转的环境空气引导到涡轮叶片的基部。 预旋转器的端壁（50,54）可以是轮廓。

公开(公告)号：US08893510B2

公开(公告)日：2014-11-25

申请号：US13670615

申请日：2012-11-07

申请人： Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

发明人： Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

IPC分类号： F02C6/04 ,  F02C7/12 ,  F01D5/08 ,  F02C7/18 ,  F01D21/00 ,  F01D25/12

CPC分类号： F02C7/18 ,  F01D5/088 ,  F01D21/00 ,  F01D25/12 ,  F05D2270/3032

摘要： An air injection system for use in a gas turbine engine includes at least one outlet port through which air is extracted from the engine only during less than full load operation, at least one rotor cooling pipe, which is used to inject the air extracted from the outlet port(s) into a rotor chamber, a piping system that provides fluid communication between the one outlet port(s) and the rotor cooling pipe(s), a blower system for extracting air from the engine through the outlet port(s) and for conveying the extracted air through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent air from passing through the piping system, and open during less than full load engine operation to allow air to pass through the piping system.

摘要翻译： 一种用于燃气涡轮发动机的空气喷射系统包括至少一个出口，通过该出口，空气仅在少于满载运行期间从发动机中抽出，至少一个转子冷却管，用于将从 出口到转子室，在一个出口和转子冷却管之间提供流体连通的管道系统，用于通过出口从发动机中提取空气的鼓风机系统， 并且将提取的空气通过管道系统和转子冷却管输送到转子室中，以及阀系统。 在全负荷发动机运行期间，阀门系统关闭，以防止空气通过管道系统，并在小于满载发动机运行期间打开以允许空气通过管道系统。

公开(公告)号：US08864452B2

公开(公告)日：2014-10-21

申请号：US13212273

申请日：2011-08-18

申请人： Kok-Mun Tham ,  Ching-Pang Lee

发明人： Kok-Mun Tham ,  Ching-Pang Lee

IPC分类号： F01D5/14

CPC分类号： F01D5/145 ,  F01D5/143 ,  F05D2240/80

摘要： In a gas turbine engine, a flow directing member includes a platform supported on a rotor, a radially facing endwall, at least one axial surface extending radially inwardly from a junction with the endwall, an airfoil extending radially outwardly from the endwall, and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface and has radially inner and outer groove ends. The outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. The groove further includes a first groove wall extending from the inner groove end to the outer groove end, and a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end.

摘要翻译： 在燃气涡轮发动机中，导流构件包括支撑在转子上的平台，径向面向的端壁，从与端壁的接合处径向向内延伸的至少一个轴向表面，从端壁径向向外延伸的翼型件和流体 流导向功能。 流体流动导向特征包括沿轴向延伸并且具有径向内部和外部凹槽端部的凹槽。 外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成用于将冷却流体引导到端壁的开口。 所述凹槽还包括从所述内槽端延伸到所述外槽端部的第一槽壁和与所述第一槽壁相对并从所述内槽端部延伸到所述外槽端部的第二槽壁。

公开(公告)号：US08721291B2

公开(公告)日：2014-05-13

申请号：US13180578

申请日：2011-07-12

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

IPC分类号： F01D5/14

CPC分类号： F01D5/081 ,  F01D5/141 ,  F05D2240/81 ,  F05D2270/17

摘要： In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.

摘要翻译： 在燃气涡轮发动机中，流动引导构件包括支撑在转子上的平台，并且包括径向面向的端壁和至少一个轴向面向轴向表面，该轴向表面从与所述端壁的连接处径向向内延伸。 导流构件还包括从端壁径向向外延伸的翼型件和流体流动引导构件。 流体流动导向特征包括轴向延伸到轴向表面的凹槽。 凹槽具有径向内槽端部和径向外槽端部，其中外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成开口，用于将冷却流体引导到端壁 。

公开(公告)号：US09061349B2

公开(公告)日：2015-06-23

申请号：US14073922

申请日：2013-11-07

申请人： Ching-Pang Lee ,  Gerald L. Hillier ,  Jae Y. Um ,  Gm Salam Azad

发明人： Ching-Pang Lee ,  Gerald L. Hillier ,  Jae Y. Um ,  Gm Salam Azad

IPC分类号： B22C9/10 ,  B22D25/02

CPC分类号： B22C9/10 ,  B22C7/02 ,  B22C7/06 ,  B22C9/04

摘要： An investment casting method for a cast ceramic core (110), including an airfoil portion (116) shaped to define an inner surface (56) of an airfoil (52) of a vane segment (50) and an integral shell portion (122) having a backside-shaping surface (120) shaped to define a backside surface (68) of a shroud (62) of the vane segment. The backside-shaping surface has a higher elevation (132) and a lower elevation (134). The higher elevation is set apart from a nearest point (138) on the airfoil portion by the lower elevation. The airfoil portion and the shell portion are cast as a monolithic body during a single casting pour.

摘要翻译： 一种用于铸造陶瓷芯（110）的熔模铸造方法，包括形成为限定叶片段（50）的翼型件（52）的内表面（56）和整体壳体部分（122）的翼型部分（116） 具有形成为限定叶片段的护罩（62）的后侧表面（68）的后侧成形表面（120）。 后侧成形表面具有较高的仰角（132）和较低的高度（134）。 较高的高度与翼面部分的最近点（138）分开，较低的高度。 翼型部分和壳体部分在单次铸造过程中作为整体式铸造。

公开(公告)号：US08920109B2

公开(公告)日：2014-12-30

申请号：US13795542

申请日：2013-03-12

申请人： Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

发明人： Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

IPC分类号： F01D25/26 ,  F02C9/16

CPC分类号： F02C9/16 ,  F01D9/06 ,  F01D11/24 ,  F01D25/10 ,  F01D25/12 ,  F05D2260/201 ,  F05D2270/3032

摘要： A thermal management arrangement (110) in a gas turbine engine (60), including: a conduit-arrangement (62) providing fluid communication between a compressor section (156) and: a relatively thermally responsive portion (52) of a turbine vane carrier (10); and a relatively thermally unresponsive portion (48) of a first turbine vane carrier. The conduit-arrangement includes: a general cooling flow outlet (122) disposed proximate the relatively thermally responsive portion of the turbine vane carrier and configured to discharge a general cooling flow (124); and an impingement flow outlet (118) disposed proximate the relatively thermally unresponsive portion and configured to discharge an impingement flow (120). The thermal management arrangement is configured such that a flow rate of the impingement flow is effective to accelerate a thermal response of the relatively thermally unresponsive portion toward a thermal response of the relatively thermally responsive portion.

摘要翻译： 一种燃气涡轮发动机（60）中的热管理装置（110），包括：导管装置（62），其在压缩机部分（156）与涡轮机叶片载体（156）的相对热响应部分（52）之间提供流体连通 （10）; 以及第一涡轮叶片载体的相对热不响应的部分（48）。 导管装置包括：一般的冷却流出口（122），其布置在涡轮叶片承载件的相对热响应部分附近并且构造成排出一般的冷却流（124）; 以及冲击流出口（118），其设置在所述相对热不响应部分附近并被配置为排出冲击流（120）。 热管理装置被配置成使得冲击流的流速有效地加速相对热不响应部分对相对热响应部分的热响应的热响应。

公开(公告)号：US20140271103A1

公开(公告)日：2014-09-18

申请号：US13795542

申请日：2013-03-12

申请人： Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

发明人： Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

IPC分类号： F02C9/16

CPC分类号： F02C9/16 ,  F01D9/06 ,  F01D11/24 ,  F01D25/10 ,  F01D25/12 ,  F05D2260/201 ,  F05D2270/3032

摘要： A thermal management arrangement (110) in a gas turbine engine (60), including: a conduit-arrangement (62) providing fluid communication between a compressor section (156) and: a relatively thermally responsive portion (52) of a turbine vane carrier (10); and a relatively thermally unresponsive portion (48) of a first turbine vane carrier. The conduit-arrangement includes: a general cooling flow outlet (122) disposed proximate the relatively thermally responsive portion of the turbine vane carrier and configured to discharge a general cooling flow (124); and an impingement flow outlet (118) disposed proximate the relatively thermally unresponsive portion and configured to discharge an impingement flow (120). The thermal management arrangement is configured such that a flow rate of the impingement flow is effective to accelerate a thermal response of the relatively thermally unresponsive portion toward a thermal response of the relatively thermally responsive portion.

摘要翻译： 一种燃气涡轮发动机（60）中的热管理装置（110），包括：导管装置（62），其在压缩机部分（156）与涡轮机叶片载体（156）的相对热响应部分（52）之间提供流体连通 （10）; 以及第一涡轮叶片载体的相对热不响应的部分（48）。 导管装置包括：一般的冷却流出口（122），其布置在涡轮叶片承载件的相对热响应部分附近并且构造成排出一般的冷却流（124）; 以及冲击流出口（118），其设置在所述相对热不响应部分附近并被配置为排出冲击流（120）。 热管理装置被配置成使得冲击流的流量有效地加速相对热不响应部分的热响应朝向相对热响应部分的热响应。

公开(公告)号：US20140147250A1

公开(公告)日：2014-05-29

申请号：US13688411

申请日：2012-11-29

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Eric Schroeder

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Eric Schroeder

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F01D5/145 ,  F01D11/001 ,  F01D11/02

摘要： A gas turbine engine, including: a plurality of blades (60) assembled into an annular row of blades and partly defining a hot gas path (26) and a cooling fluid path (24), wherein the cooling fluid path extends from a rotor cavity (22) to the hot gas path; an angel wing assembly (99) disposed on a side (74) of a base (76) of the row of blades; and pumping features (130) distributed about the angel wing assembly configured to impart, at a narrowest gap (42) of the cooling fluid path, motion to a flow of cooling fluid flowing there through. The plurality of pumping features, the angel wing assembly, and the base of the row of blades are effective to produce a helical motion to the flow of cooling fluid as it enters the hot gas path.

摘要翻译： 一种燃气涡轮发动机，包括：多个叶片（60），其组装成环形叶片的叶片并且部分地限定热气体路径（26）和冷却流体路径（24），其中冷却流体路径从转子腔 （22）到热气路径; 设置在所述一排叶片的基部（76）的侧面（74）上的天使翼组件（99） 以及围绕天使翼组件分布的泵送特征（130），其被配置为在冷却流体路径的最窄间隙（42）处施加对流过其的冷却流体流的运动。 多个泵送特征，天使翼组件和叶片排的基部有效地在冷却流体进入热气体路径时产生螺旋运动。

公开(公告)号：US20130017095A1

公开(公告)日：2013-01-17

申请号：US13180578

申请日：2011-07-12

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

IPC分类号： F01D5/14

CPC分类号： F01D5/081 ,  F01D5/141 ,  F05D2240/81 ,  F05D2270/17

摘要： In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.

摘要翻译： 在燃气涡轮发动机中，流动引导构件包括支撑在转子上的平台，并且包括径向面向的端壁和至少一个轴向面向轴向表面，该轴向表面从与所述端壁的连接处径向向内延伸。 导流构件还包括从端壁径向向外延伸的翼型件和流体流动引导构件。 流体流动导向特征包括轴向延伸到轴向表面的凹槽。 凹槽具有径向内槽端部和径向外槽端部，其中外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成开口，用于将冷却流体引导到端壁 。

公开(公告)号：US20120183389A1

公开(公告)日：2012-07-19

申请号：US13005752

申请日：2011-01-13

申请人： Shantanu P. Mhetras ,  Manjit Shivanand ,  Abdullatif M. Chehab ,  Ching-Pang Lee

发明人： Shantanu P. Mhetras ,  Manjit Shivanand ,  Abdullatif M. Chehab ,  Ching-Pang Lee

IPC分类号： F01D5/18

CPC分类号： F01D5/3015

摘要： A sealing system for a rotor assembly in a gas turbine engine is disclosed. The sealing system may include a seal formed from a side block and an upper seal that seals a gap between a radially outward extending first rotor supply channel in a rotor assembly terminating at an inlet of an axially extending second rotor supply channel that is in fluid communication with an internal blade cooling system of a turbine blade. The seal may include components that enhance the flow of cooling fluids over conventional configurations. In another embodiment, the sealing system may include an integrated sealing block configured to seal a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels. The integrated sealing block may be formed from a radially inward extending leg and central body.

摘要翻译： 公开了一种用于燃气涡轮发动机中的转子组件的密封系统。 密封系统可以包括由侧块形成的密封件和上密封件，其密封位于轴向延伸的第二转子供应通道的入口处的转子组件中的径向向外延伸的第一转子供应通道之间的间隙，该第二转子供应通道处于流体连通 具有涡轮叶片的内部叶片冷却系统。 密封件可以包括增强冷却流体超过常规结构的流动的部件。 在另一个实施例中，密封系统可以包括集成密封块，其被配置为在第一和第二转子供应通道之间的交叉处密封相邻涡轮叶片之间的间隙。 集成密封块可以由径向向内延伸的腿和中心体形成。