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1. 发明申请

US20150122450A1 Ceramic casting core having an integral vane internal core and shroud backside shell for vane segment casting 审中-公开
标题翻译：陶瓷铸芯具有一体的叶片内芯和用于叶片段铸造的罩背后壳
公开(公告)号：US20150122450A1
公开(公告)日：2015-05-07
申请号：US13998541
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： B22C9/24 , B22C9/10
CPC分类号： B22C9/24 , B22C7/06 , B22C9/04 , B22C9/10 , F01D5/188 , F01D9/041 , F05D2260/201
摘要： 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 a 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：一种铸造陶瓷芯（110），包括：形成为限定叶片段（50）的翼型件（52）的内表面（56）的翼型部分（116）以及壳体部分（122），其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。

2. 发明申请

US20150122446A1 INVESTMENT CASTING METHOD FOR GAS TURBINE ENGINE VANE SEGMENT 有权
标题翻译：燃气轮机发动机分段投资方法
公开(公告)号：US20150122446A1
公开(公告)日：2015-05-07
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： B22D25/02 , B22C9/10
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。

3. 发明授权

US09061349B2 Investment casting method for gas turbine engine vane segment 有权
标题翻译：燃气轮机叶片段投资铸造方法
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。

4. 发明授权

US09062557B2 Flow discourager integrated turbine inter-stage U-ring 有权
标题翻译：整流式涡轮机级U型环
公开(公告)号：US09062557B2
公开(公告)日：2015-06-23
申请号：US13226547
申请日：2011-09-07
申请人： Kok-Mun Tham , Ching-Pang Lee , Abdullatif M. Chehab , Gm Salam Azad , Shantanu P. Mhetras , Manjit Shivanand , Vincent P. Laurello , Christopher Rawlings
发明人： Kok-Mun Tham , Ching-Pang Lee , Abdullatif M. Chehab , Gm Salam Azad , Shantanu P. Mhetras , Manjit Shivanand , Vincent P. Laurello , Christopher Rawlings
IPC分类号： F01D1/02 , F01D11/00 , F01D11/04
CPC分类号： F01D11/001 , F01D11/04
摘要： A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).
摘要翻译：一种具有转子盘（9），延伸到盘腔（13）的盘腔（13）和定子级（25）的燃气轮机。密封壳体凸缘（43,44）从定子台（25）的密封壳体（29）延伸。转子凸缘（41i，41o）从转子盘（9-1）延伸。内转子凸缘（41i）和第一密封壳体凸缘（43）从第二密封壳体凸缘（44）向内。一个转子凸缘（41o）从第二密封壳体凸缘（44）向外。内转子凸缘（41i）和第一密封壳体凸缘（43）朝向彼此延伸以限制主气流（17）的移动。入口（47）在外转子凸缘（41o）和第二密封壳体凸缘（44）之间注入空气（50）。

5. 发明申请

US20120177479A1 INNER SHROUD COOLING ARRANGEMENT IN A GAS TURBINE ENGINE 审中-公开
标题翻译：内燃机内燃机冷却装置
公开(公告)号：US20120177479A1
公开(公告)日：2012-07-12
申请号：US12985571
申请日：2011-01-06
申请人： Gm Salam Azad , Ching-Pang Lee , Zhihong Gao
发明人： Gm Salam Azad , Ching-Pang Lee , Zhihong Gao
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/041 , F05D2240/59 , F05D2240/81 , F05D2260/202 , F05D2260/60
摘要： A component in a gas turbine engine includes an airfoil and a shroud. The shroud has an outer surface supporting an end of the airfoil and defines a portion of an annular gas path. The shroud includes axial edges extending between upstream and downstream edges thereof. Each of the axial edges includes a seal slot that receives a seal member extending between the shroud and an adjacent shroud. A cooling air channel extends between the upstream and downstream edges of the shroud. A cooling air supply passage extends from a cooling air chamber at an inner surface of the shroud to the cooling air channel. At least one cooling air exit passage extends from the cooling air channel to one of the axial edges. The cooling air channel is located radially between the outer surface of the shroud and the seal slot.
摘要翻译：燃气涡轮发动机中的部件包括翼型件和护罩。护罩具有支撑翼型件端部的外表面并且限定环形气体路径的一部分。护罩包括在其上游边缘和下游边缘之间延伸的轴向边缘。每个轴向边缘包括一个密封槽，该密封槽容纳在护罩和相邻护罩之间延伸的密封件。冷却空气通道在护罩的上游和下游边缘之间延伸。冷却空气供给通道从罩的内表面处的冷却空气室延伸到冷却空气通道。至少一个冷却空气出口通道从冷却空气通道延伸到轴向边缘之一。冷却空气通道径向地位于护罩的外表面和密封槽之间。

6. 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。

7. 发明申请

US20140321980A1 COOLING SYSTEM INCLUDING WAVY COOLING CHAMBER IN A TRAILING EDGE PORTION OF AN AIRFOIL ASSEMBLY 有权
标题翻译：包括波纹冷却室的冷却系统在航空货架总成的尾部
公开(公告)号：US20140321980A1
公开(公告)日：2014-10-30
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。

8. 发明授权

US08939711B2 Outer rim seal assembly in a turbine engine 有权
标题翻译：涡轮发动机中的外轮缘密封组件
公开(公告)号：US08939711B2
公开(公告)日：2015-01-27
申请号：US13768561
申请日：2013-02-15
申请人： Ching-Pang Lee , Kok-Mun Tham , Manjit Shivanand , Vincent P. Laurello , Gm Salam Azad , Nicholas F. Martin, Jr.
发明人： Ching-Pang Lee , Kok-Mun Tham , Manjit Shivanand , Vincent P. Laurello , Gm Salam Azad , Nicholas F. Martin, Jr.
IPC分类号： F01D25/12 , F01D5/08 , F01D11/04
CPC分类号： F01D25/12 , F01D5/081 , F01D11/001 , F01D11/04 , F01D11/122 , F05D2260/202
摘要： A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.
摘要翻译：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不可旋转的叶片组件，其包括一排叶片和内部护罩，与叶片组件相邻的可旋转刀片组件，并且包括一排叶片和形成涡轮机转子的一部分的涡轮盘，以及径向位于热气路径和盘腔之间的环形翼部件。翼构件大致轴向地从叶片组件延伸到叶片组件，并且包括从其径向内表面延伸到其径向外表面的多个周向间隔开的流动通道。在发动机运行期间，流动通道将冷却流体从盘腔抽吸到热气路径。

9. 发明申请

US20140234076A1 OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE 有权
标题翻译：涡轮发动机中的外部密封组件
公开(公告)号：US20140234076A1
公开(公告)日：2014-08-21
申请号：US13768561
申请日：2013-02-15
申请人： Ching-Pang Lee , Kok-Mun Tham , Manjit Shivanand , Vincent P. Laurello , Gm Salam Azad , Nicholas F. Martin, JR.
发明人： Ching-Pang Lee , Kok-Mun Tham , Manjit Shivanand , Vincent P. Laurello , Gm Salam Azad , Nicholas F. Martin, JR.
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/081 , F01D11/001 , F01D11/04 , F01D11/122 , F05D2260/202
摘要： A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.
摘要翻译：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不可旋转的叶片组件，其包括一排叶片和内部护罩，与叶片组件相邻的可旋转刀片组件，并且包括一排叶片和形成涡轮机转子的一部分的涡轮盘，以及径向位于热气路径和盘腔之间的环形翼部件。翼构件大致轴向地从叶片组件延伸到叶片组件，并且包括从其径向内表面延伸到其径向外表面的多个周向间隔开的流动通道。在发动机运行期间，流动通道将冷却流体从盘腔抽吸到热气路径。

10. 发明授权

US08608443B2 Film cooled component wall in a turbine engine 有权
标题翻译：涡轮发动机中的薄膜冷却部件壁
公开(公告)号：US08608443B2
公开(公告)日：2013-12-17
申请号：US12813602
申请日：2010-06-11
申请人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
发明人： Ching-Pang Lee , Jae Y. Um , Mrinal Munshi , Humberto A. Zuniga
IPC分类号： F01D9/06 , F01D5/18
CPC分类号： F01D5/186 , F01D5/288 , F01D25/12 , F05D2230/10 , F05D2230/30 , F05D2230/90 , F05D2250/183 , F05D2250/185 , F05D2260/202 , F05D2260/221 , F05D2300/502 , F23R2900/03042 , Y10T29/49236
摘要： A component wall in a turbine engine. The component wall includes a substrate, a trench, and a plurality of cooling passages. The substrate has a first surface and a second surface opposed from the first surface. The trench is located in the second surface and is defined by a bottom surface between the first and second surfaces, a first sidewall, and a second sidewall spaced from the first sidewall. The first sidewall extends radially outwardly continuously from the bottom surface of the trench to the second surface. The first sidewall includes a plurality of first protuberances extending toward the second sidewall. The cooling passages extend through the substrate from the first surface to the bottom surface of the trench. Outlets of the cooling passages are arranged within the trench such that cooling air exiting the cooling passages is directed toward respective ones of the first protuberances.
摘要翻译：涡轮发动机中的部件壁。部件壁包括基板，沟槽和多个冷却通道。基板具有与第一表面相对的第一表面和第二表面。沟槽位于第二表面中，并且由第一和第二表面之间的底表面，第一侧壁和与第一侧壁间隔开的第二侧壁限定。第一侧壁从沟槽的底表面连续径向向外延伸到第二表面。第一侧壁包括朝向第二侧壁延伸的多个第一突起。冷却通道从沟槽的第一表面延伸到底表面。冷却通道的出口布置在沟槽内，使得离开冷却通道的冷却空气被引向第一突起中的相应的一个。

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