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1. 发明授权

US09017014B2 Aft outer rim seal arrangement 有权
标题翻译：后外缘密封布置
公开(公告)号：US09017014B2
公开(公告)日：2015-04-28
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： F01D11/08 , F01D25/12 , 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。

2. 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。

3. 发明授权

US08926267B2 Ambient air cooling arrangement having a pre-swirler for gas turbine engine blade cooling 有权
标题翻译：环境空气冷却装置具有用于燃气涡轮发动机叶片冷却的预旋转器
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。

4. 发明申请

US20130156579A1 AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING 有权
标题翻译：具有用于气体涡轮发动机叶片冷却器的预吹扫器的环境空气冷却装置
公开(公告)号：US20130156579A1
公开(公告)日：2013-06-20
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： F01D5/18 , F01D25/12
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。

5. 发明授权

US08926283B2 Turbine blade angel wing with pumping features 有权
标题翻译：涡轮叶片天使翼具有抽水功能
公开(公告)号：US08926283B2
公开(公告)日：2015-01-06
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： F01D11/00 , F01D5/14 , F01D11/02
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。

6. 发明申请

US20140147250A1 TURBINE BLADE ANGEL WING WITH PUMPING FEATURES 有权
标题翻译：涡轮叶片天鹅绒与抽水功能
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。

7. 发明授权

US08820091B2 External cooling fluid injection system in a gas turbine engine 有权
标题翻译：燃气涡轮发动机中的外部冷却液喷射系统
公开(公告)号：US08820091B2
公开(公告)日：2014-09-02
申请号：US13670788
申请日：2012-11-07
申请人： Kok-Mun Tham , Ching-Pang Lee , Vincent P. Laurello , Abdullatif M. Chehab , David A. Kemp , John A. Fussner , Yan Yin , Bijay K. Sultanian , Weidong Cai
发明人： Kok-Mun Tham , Ching-Pang Lee , Vincent P. Laurello , Abdullatif M. Chehab , David A. Kemp , John A. Fussner , Yan Yin , Bijay K. Sultanian , Weidong Cai
IPC分类号： F02C6/04 , F02C7/12
CPC分类号： F02C7/12 , F01D5/088 , F01D21/00 , F01D25/12 , F01D25/34 , F05D2270/3032
摘要： A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid 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 cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.
摘要翻译：用于燃气涡轮发动机的冷却流体空气喷射系统包括在外部冷却流体源处的至少一个转子冷却管，其用于将来自所述源的冷却流体注入到转子室中;提供流体连通的管道系统在源和转子冷却管之间，用于将冷却流体通过管道系统和转子冷却管输送到转子室中的鼓风机系统和阀系统。在全负载发动机运行期间，阀系统关闭，以防止来自源的冷却流体通过管道系统，并且在小于满载发动机运行期间打开以允许来自源的冷却流体通过管道系统。

8. 发明申请

US20140123675A1 AIR INJECTION SYSTEM IN A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机空气喷射系统
公开(公告)号：US20140123675A1
公开(公告)日：2014-05-08
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： F02C7/18
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。

9. 发明申请

US20140123657A1 EXTERNAL COOLING FLUID INJECTION SYSTEM IN A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机外部冷却流体注入系统
公开(公告)号：US20140123657A1
公开(公告)日：2014-05-08
申请号：US13670788
申请日：2012-11-07
申请人： Kok-Mun Tham , Ching-Pang Lee , Vincent P. Laurello , Abdullatif M. Chehab , David A. Kemp , John A. Fussner , Yan Yin , Bijay K. Sultanian , Weidong Cai
发明人： Kok-Mun Tham , Ching-Pang Lee , Vincent P. Laurello , Abdullatif M. Chehab , David A. Kemp , John A. Fussner , Yan Yin , Bijay K. Sultanian , Weidong Cai
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D5/088 , F01D21/00 , F01D25/12 , F01D25/34 , F05D2270/3032
摘要： A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid 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 cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.
摘要翻译：用于燃气涡轮发动机的冷却流体空气喷射系统包括在外部冷却流体源处的至少一个转子冷却管，其用于将来自所述源的冷却流体注入到转子室中;提供流体连通的管道系统在源和转子冷却管之间，用于将冷却流体通过管道系统和转子冷却管输送到转子室中的鼓风机系统和阀系统。在全负载发动机运行期间，阀系统关闭，以防止来自源的冷却流体通过管道系统，并且在小于满载发动机运行期间打开以允许来自源的冷却流体通过管道系统。

10. 发明申请

US20130017080A1 FLOW DIRECTING MEMBER FOR GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的流动导向构件
公开(公告)号：US20130017080A1
公开(公告)日：2013-01-17
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： F01D9/02
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。

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