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1. 发明授权

US08684684B2 Turbine assembly with end-wall-contoured airfoils and preferenttial clocking 有权
标题翻译：涡轮机组件，具有端壁波纹的翼型和不均匀的时钟
公开(公告)号：US08684684B2
公开(公告)日：2014-04-01
申请号：US12872770
申请日：2010-08-31
申请人： Jeffrey Donald Clements , Vidhu Shekhar Pandey , Ching-Pang Lee
发明人： Jeffrey Donald Clements , Vidhu Shekhar Pandey , Ching-Pang Lee
IPC分类号： F01D1/02
CPC分类号： F01D9/041 , F01D5/143
摘要： A turbine apparatus includes: A first nozzle comprising an array of first vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; A rotor downstream from the first nozzle comprising a plurality of blades carried by a rotatable disk; and a second nozzle disposed downstream from the rotor comprising an array of second vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; wherein the first and second vanes of the first and second nozzles are circumferentially clocked relative to each other such that, in a predetermined operating condition, wakes discharged from the first vanes are aligned in a circumferential direction with the leading edges of the second vanes, wherein a stacking axis of the first vanes is nonlinear. An inner band of the first nozzle is contoured in a non-axisymmetric shape.
摘要翻译：涡轮装置包括：第一喷嘴，包括第一叶片阵列，每个叶片包括凹压侧，凸吸入侧，以及前缘和后缘; 第一喷嘴下游的转子包括由可旋转盘承载的多个叶片; 以及设置在所述转子的下游的第二喷嘴，包括第二叶片的阵列，每个叶片包括凹压侧，凸吸入侧以及前缘和后缘; 其中所述第一和第二喷嘴的所述第一和第二叶片相对于彼此沿圆周方向定时，使得在预定操作条件下，从所述第一叶片排出的骤冷器沿周向与所述第二叶片的前缘对齐，其中第一叶片的堆叠轴线是非线性的。第一喷嘴的内带是非轴对称的形状。

2. 发明授权

US08459956B2 Curved platform turbine blade 有权
标题翻译：弯曲平台涡轮叶片
公开(公告)号：US08459956B2
公开(公告)日：2013-06-11
申请号：US12344058
申请日：2008-12-24
申请人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
发明人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F01D5/3007 , F05D2240/80 , F05D2270/17 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.
摘要翻译：涡轮机叶片包括在其根部处的翼型件和整体式平台。该平台的立面从脊到波纹形状，并且轴向弯曲以补充下一个相邻的弯曲平台。

3. 发明申请

US20120051930A1 SHROUDED TURBINE BLADE WITH CONTOURED PLATFORM AND AXIAL DOVETAIL 审中-公开
标题翻译： SHROUDED涡轮叶片与轮廓平台和轴向DOVETAIL
公开(公告)号：US20120051930A1
公开(公告)日：2012-03-01
申请号：US12872827
申请日：2010-08-31
申请人： Vidhu Shekhar Pandey , Ching-Pang Lee , Aspi Rustom Wadia , Jeffrey Donald Clements
发明人： Vidhu Shekhar Pandey , Ching-Pang Lee , Aspi Rustom Wadia , Jeffrey Donald Clements
IPC分类号： F04D29/38
CPC分类号： F01D5/145 , F01D5/143 , F01D5/3007 , F05D2240/80
摘要： A turbine blade includes an airfoil having a root, a tip, a concave pressure side, and a laterally opposite convex suction side, the pressure and suction sides extending in chord between opposite leading and trailing edges; an outer platform disposed at the tip of the airfoil, the outer platform having spaced-apart lateral edges which each define an interlocking element; an inner platform with two spaced-apart curved lateral edges disposed at the root of the airfoil, the inner platform having a hot side facing the airfoil which is contoured in a non-axisymmetric shape; and a dovetail extending radially inward from the opposite side of the inner platform, wherein the dovetail is axially straight.
摘要翻译：涡轮叶片包括具有根部，顶端，凹形压力侧和横向相对的凸形吸入侧的翼型件，压力和吸力侧在相对的前缘和后缘之间延伸成弦; 设置在所述翼型件的尖端处的外平台，所述外平台具有间隔开的横向边缘，每个边缘限定互锁元件; 内平台，其具有设置在翼型的根部处的两个间隔开的弯曲侧边缘，内平台具有面向翼型的热侧，其以非轴对称的形状成型; 以及从内平台的相对侧径向向内延伸的燕尾榫，其中燕尾轴向是直的。

4. 发明申请

US20100143139A1 BANKED PLATFORM TURBINE BLADE 有权
标题翻译： BANKED平台涡轮叶片
公开(公告)号：US20100143139A1
公开(公告)日：2010-06-10
申请号：US12330783
申请日：2008-12-09
申请人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
发明人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
IPC分类号： F01D5/22 , F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a bank adjacent the pressure side of the airfoil to a trough commencing behind the airfoil leading edge.
摘要翻译：涡轮机叶片包括在其根部处的翼型件和整体式平台。平台的高度是从靠近翼型的压力侧的一个堤岸到从翼型前缘的后面开始的槽。

5. 发明申请

US20120051894A1 TURBINE ASSEMBLY WITH END-WALL-CONTOURED AIRFOILS AND PREFERENTTIAL CLOCKING 有权
标题翻译：涡轮组件，带有端壁式空气和优选时钟
公开(公告)号：US20120051894A1
公开(公告)日：2012-03-01
申请号：US12872770
申请日：2010-08-31
申请人： Jeffrey Donald Clements , Vidhu Shekhar Pandey , Ching-Pang Lee
发明人： Jeffrey Donald Clements , Vidhu Shekhar Pandey , Ching-Pang Lee
IPC分类号： F04D29/44
CPC分类号： F01D9/041 , F01D5/143
摘要： A turbine apparatus includes: A first nozzle comprising an array of first vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; A rotor downstream from the first nozzle comprising a plurality of blades carried by a rotatable disk; and a second nozzle disposed downstream from the rotor comprising an array of second vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; wherein the first and second vanes of the first and second nozzles are circumferentially clocked relative to each other such that, in a predetermined operating condition, wakes discharged from the first vanes are aligned in a circumferential direction with the leading edges of the second vanes, wherein a stacking axis of the first vanes is nonlinear. An inner band of the first nozzle is contoured in a non-axisymmetric shape.
摘要翻译：涡轮装置包括：第一喷嘴，包括第一叶片阵列，每个叶片包括凹压侧，凸吸入侧，以及前缘和后缘; 第一喷嘴下游的转子包括由可旋转盘承载的多个叶片; 以及设置在所述转子的下游的第二喷嘴，包括第二叶片的阵列，每个叶片包括凹压侧，凸吸入侧以及前缘和后缘; 其中所述第一和第二喷嘴的所述第一和第二叶片相对于彼此沿圆周方向定时，使得在预定操作条件下，从所述第一叶片排出的骤冷器沿周向与所述第二叶片的前缘对齐，其中第一叶片的堆叠轴线是非线性的。第一喷嘴的内带是非轴对称的形状。

6. 发明申请

US20100158696A1 CURVED PLATFORM TURBINE BLADE 有权
标题翻译：弯曲平台涡轮叶片
公开(公告)号：US20100158696A1
公开(公告)日：2010-06-24
申请号：US12344058
申请日：2008-12-24
申请人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
发明人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F01D5/3007 , F05D2240/80 , F05D2270/17 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.
摘要翻译：涡轮机叶片包括在其根部处的翼型件和整体式平台。该平台的立面从脊到波纹形状，并且轴向弯曲以补充下一个相邻的弯曲平台。

7. 发明授权

US08647067B2 Banked platform turbine blade 有权
标题翻译：平台涡轮叶片
公开(公告)号：US08647067B2
公开(公告)日：2014-02-11
申请号：US12330783
申请日：2008-12-09
申请人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
发明人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
IPC分类号： B63H1/26 , B63H1/16
CPC分类号： F01D5/145 , F01D5/143 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a bank adjacent the pressure side of the airfoil to a trough commencing behind the airfoil leading edge.
摘要翻译：涡轮机叶片包括在其根部处的翼型件和整体式平台。平台的高度是从靠近翼型的压力侧的一个堤岸到从翼型前缘的后面开始的槽。

8. 发明申请

US20120051900A1 TURBINE NOZZLE WITH CONTOURED BAND 有权
标题翻译：涡轮喷嘴带轮廓带
公开(公告)号：US20120051900A1
公开(公告)日：2012-03-01
申请号：US12872485
申请日：2010-08-31
申请人： Jeffery Donald Clements , Vidhu Shekhar Pandey , Ching-Pang Lee
发明人： Jeffery Donald Clements , Vidhu Shekhar Pandey , Ching-Pang Lee
IPC分类号： F01D1/02
CPC分类号： F01D9/02 , F01D9/04
摘要： A turbine nozzle includes an array of turbine vanes between inner and outer bands. Each vane includes opposed pressure and suction sides extending between opposed leading and trailing edges. The vanes define a plurality of flow passages each of which is bounded between the inner band, the outer band, and adjacent first and second vanes. A surface of the inner band in each of the passages is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of the first vane adjacent its leading edge, and a trough of relatively lower radial height is disposed parallel to and spaced-away from the suction side of the second vane aft of its leading edge. The peak and trough define cooperatively define an arcuate channel extending axially along the inner band between the first and second vanes.
摘要翻译：涡轮喷嘴包括在内带和外带之间的涡轮叶片阵列。每个叶片包括在相对的前缘和后缘之间延伸的相对的压力和吸力侧。叶片限定多个流动通道，每个流动通道限定在内带，外带和相邻的第一和第二叶片之间。每个通道中的内带表面的轮廓是非轴对称的形状，包括邻近第一叶片邻近其前缘的压力侧相对较高的径向高度的峰，并且设置相对较低径向高度的槽平行于其前缘的第二叶片后部的吸入侧并与其间隔开。峰和槽限定协同地限定沿着第一和第二叶片之间的内带轴向延伸的弓形通道。

9. 发明授权

US08727716B2 Turbine nozzle with contoured band 有权
标题翻译：涡轮喷嘴带轮廓带
公开(公告)号：US08727716B2
公开(公告)日：2014-05-20
申请号：US12872485
申请日：2010-08-31
申请人： Jeffrey Donald Clements , Vidhu Skekhar Pandey , Ching-Pang Lee
发明人： Jeffrey Donald Clements , Vidhu Skekhar Pandey , Ching-Pang Lee
IPC分类号： F01D9/04
CPC分类号： F01D9/02 , F01D9/04
摘要： A turbine nozzle includes an array of turbine vanes between inner and outer bands. Each vane includes opposed pressure and suction sides extending between opposed leading and trailing edges. The vanes define a plurality of flow passages each of which is bounded between the inner band, the outer band, and adjacent first and second vanes. A surface of the inner band in each of the passages is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of the first vane adjacent its leading edge, and a trough of relatively lower radial height is disposed parallel to and spaced-away from the suction side of the second vane aft of its leading edge. The peak and trough define cooperatively define an arcuate channel extending axially along the inner band between the first and second vanes.
摘要翻译：涡轮喷嘴包括在内带和外带之间的涡轮叶片阵列。每个叶片包括在相对的前缘和后缘之间延伸的相对的压力和吸力侧。叶片限定多个流动通道，每个流动通道限定在内带，外带和相邻的第一和第二叶片之间。每个通道中的内带表面的轮廓是非轴对称的形状，包括邻近第一叶片邻近其前缘的压力侧相对较高的径向高度的峰，并且设置相对较低径向高度的槽平行于其前缘的第二叶片后部的吸入侧并与其间隔开。峰和槽限定协同地限定沿着第一和第二叶片之间的内带轴向延伸的弓形通道。

10. 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.

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