公开(公告)号：US20050111977A1

公开(公告)日：2005-05-26

申请号：US10718465

申请日：2003-11-20

Applicant: Ching-Pang Lee ,  Steven Brassfield ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Steven Brassfield ,  Chander Prakash

IPC: F01D5/18 ,  F02C7/18 ,  B63H1/14

CPC classification number: F01D5/187 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.

Abstract translation: 涡轮叶片包括具有在前缘和后缘之间延伸的压力和吸力侧壁以及从根部到尖端的翼型件。 燕尾榫在平台上连接到翼型根部。 三个内部冷却回路在翼型内部的跨度上延伸，并且每个回路包括相应的入口通道，其从燕尾榫开始轴向相邻对准。 入口通道从燕尾榫通过平台扭转在一起，并且横跨相邻的侧壁横向相邻对齐，并进入前缘的后翼。

公开(公告)号：US4077683A

公开(公告)日：1978-03-07

申请号：US669400

申请日：1976-03-22

Applicant: Chander Prakash Bhateja ,  Richard Lassen Alling

Inventor： Chander Prakash Bhateja ,  Richard Lassen Alling

IPC: F16C19/30 ,  F16C33/46

CPC classification number: F16C33/4623 ,  F16C19/305

Abstract: The roller thrust bearing cage and roller assembly includes an annular cage with a plurality of circumferentially spaced pockets. Each of the pockets is shaped to give proper guidance to the roller when the extended center line of the roller passes through the axis of the annular cage. Preferably each pocket has two radially, inwardly converging sides and preferably, the pockets are trapezoidal. A cylindrical roller is preferably located in each of the pockets.

Abstract translation: 滚子推力轴承保持架和滚子组件包括具有多个周向间隔开的凹部的环形保持架。 当辊的延长的中心线穿过环形笼的轴线时，每个袋都成形为能够适当地引导辊。 优选地，每个袋具有两个径向向内会聚的侧面，并且优选地，所述袋是梯形的。 优选地，圆柱滚子位于每个凹穴中。

公开(公告)号：US08721291B2

公开(公告)日：2014-05-13

申请号：US13180578

申请日：2011-07-12

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

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

IPC: F01D5/14

CPC classification number: F01D5/081 ,  F01D5/141 ,  F05D2240/81 ,  F05D2270/17

Abstract: 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.

Abstract translation: 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：US07806653B2

公开(公告)日：2010-10-05

申请号：US11615556

申请日：2006-12-22

Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

IPC: F01D9/00

CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D9/041 ,  F05D2240/301 ,  F05D2250/611 ,  F05D2250/71 ,  Y02T50/673

Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.

Abstract translation: 可用于发动机组件的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处联接到第一侧壁。 翼型件从根部径向延伸到尖端部分。 前缘和后缘中的每一个包括在根部部分和尖端部分之间限定的至少一个瘦方向改变和多个扫掠方向改变。

公开(公告)号：US20080148564A1

公开(公告)日：2008-06-26

申请号：US11615514

申请日：2006-12-22

Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

IPC: F01D5/02

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49236

Abstract: A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.

Abstract translation: 一种用于燃气涡轮发动机的涡轮组件。 涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。 定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。 翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。 涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。 叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。 与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。

公开(公告)号：US06672829B1

公开(公告)日：2004-01-06

申请号：US10196623

申请日：2002-07-16

Applicant: David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

Inventor： David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

IPC: F01D518

CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D5/20 ,  F05D2250/292

Abstract: A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.

Abstract translation: 一种用于燃气涡轮发动机的涡轮机叶片，包括翼型件和整体式燕尾榫，用于将翼型件沿着径向轴线安装到涡轮机外罩内侧的转子盘。 所述翼型件还包括：在前缘和后缘处连接在一起的第一和第二侧壁，其中所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到顶板，用于在其上引导燃烧气体; 以及在前缘和后缘之间从顶板向外延伸的至少一个尖端肋。 尖端肋被定向成使得纵向延伸通过的轴线相对于径向轴线成一定角度，用于涡轮叶片的至少一个轴向长度的指定部分。 这种角度在指定部分可以是基本相同的，或者可以在其上变化。 因此，燃烧气体的再循环区域形成在尖端肋的远端附近，这减少了涡轮叶片至少轴向长度的指定部分的翼型和护罩之间的燃烧气体的泄漏流。

公开(公告)号：US06382913B1

公开(公告)日：2002-05-07

申请号：US09783279

申请日：2001-02-09

Applicant: Ching-Pang Lee ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Chander Prakash

IPC: F01D518

CPC classification number: F01D5/20 ,  F01D5/141 ,  F01D5/186 ,  F05D2250/70 ,  F05D2260/202

Abstract: A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A portion of the second tip wall is recessed to define a tip shelf that extends from the airfoil leading edge to the airfoil trailing edge.

Abstract translation: 描述了一种用于燃气涡轮发动机的转子叶片，其包括有助于降低转子叶片的操作温度的尖端区域。 尖端区域包括从翼型件的顶板径向向外延伸的第一顶端壁和第二顶端壁。 尖端壁从翼型的前缘相邻延伸，以在翼型的后缘连接。 第二顶壁的一部分是凹进的，以限定从翼型件前缘延伸到翼型后缘的尖端架。