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1. 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。

2. 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。

3. 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。

4. 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。

5. 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。

6. 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。

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. 发明授权

US07819626B2 Plasma blade tip clearance control 有权
标题翻译：等离子叶片顶端间隙控制
公开(公告)号：US07819626B2
公开(公告)日：2010-10-26
申请号：US11580789
申请日：2006-10-13
申请人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Scott Michael Carson
发明人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Scott Michael Carson
IPC分类号： F01D11/20 , F01D11/24
CPC分类号： F01D11/20 , F05D2270/172 , Y02T50/671 , Y10S415/914
摘要： A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generator is mounted to the annular shroud and includes radially inner and outer electrodes separated by a dielectric material disposed within an annular groove in a radially inwardly facing surface of the annular shroud. The plasma generator is operable for producing an annular plasma between the annular shroud and blade tips and an effective clearance produced by the annular plasma between the annular shroud and blade tips that is smaller than a clearance between the annular shroud and blade tips.
摘要翻译：燃气涡轮发动机等离子体叶片顶端间隙控制系统包括围绕可旋转叶片尖端的环形护罩和沿径向向外并与叶片尖端分开的环形等离子体发生器。环形等离子体发生器的示例性实施例安装到环形护罩，并且包括径向内部和外部电极，该电极由设置在环形护罩的径向向内的表面中的环形槽内的电介质材料隔开。等离子体发生器可操作用于在环形护罩和叶片尖端之间产生环形等离子体，以及由环形护罩和叶片尖端之间的环形等离子体产生的有效间隙小于环形罩和叶片尖端之间的间隙。

9. 发明申请

US20090155088A1 DUST HOLE DOME BLADE 有权
公开(公告)号：US20090155088A1
公开(公告)日：2009-06-18
申请号：US11494378
申请日：2006-07-27
申请人： Ching-Pang Lee , Tingfan Pang , Brian Alan Norton , Jan Christopher Schilling , Aspi Rustom Wadia
发明人： Ching-Pang Lee , Tingfan Pang , Brian Alan Norton , Jan Christopher Schilling , Aspi Rustom Wadia
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/20 , F05D2240/122 , F05D2240/304 , F05D2240/307 , F05D2250/185 , F05D2260/20 , F05D2260/202 , F05D2260/2212 , F05D2260/607 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil.
摘要翻译：中空涡轮机翼型件包括在相对的压力侧壁和抽吸侧壁之间限定内部冷却回路的顶盖。顶盖包括围绕灰尘孔的内部圆顶，并且圆顶向外朝向翼型根部横向地在相对的侧壁之间向上倾斜，并且在翼型的相对的前缘和后缘之间弦向地倾斜。

10. 发明申请

US20080145233A1 Plasma induced virtual turbine airfoil trailing edge extension 失效
标题翻译：等离子体引起的虚拟涡轮机翼缘后缘延伸
公开(公告)号：US20080145233A1
公开(公告)日：2008-06-19
申请号：US11639878
申请日：2006-12-15
申请人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Je-Chin Han
发明人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Je-Chin Han
IPC分类号： F01D5/12 , F01D17/00
CPC分类号： F01D5/147 , F01D5/145 , F01D9/041 , F05D2240/122 , F05D2240/304 , F05D2270/172 , Y02T50/673 , Y10S415/914
摘要： A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on an outer wall of the airfoil with first and second pluralities of the plasma generators on pressure and suction sides of the airfoil respectively. The plasma generators may include inner and outer electrodes separated by a dielectric material disposed within a grooves in an outer hot surface of the outer wall of the airfoil. The plasma generators may be located at an aft end of the airfoil and the inner electrodes flush with the trailing edge base. A method for operating the system includes energizing one or more of plasma generators in steady state or unsteady modes.
摘要翻译：后缘涡流减少系统包括在翼展方向上延伸的燃气涡轮发动机翼型件，在翼型件的后缘周围的后缘区域中的一个或多个翼展方向延伸的等离子体发生器。等离子体发生器可以分别安装在机翼的外壁上，其中第一和第二多个等离子体发生器分别在翼型的压力和吸力侧。等离子体发生器可以包括由设置在翼型件的外壁的外部热表面中的凹槽内的介电材料隔开的内部和外部电极。等离子体发生器可以位于翼型的后端，并且内部电极与后缘基座齐平。用于操作该系统的方法包括给稳态或不稳定模式中的一个或多个等离子体发生器通电。

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