公开(公告)号：US20110150653A1

公开(公告)日：2011-06-23

申请号：US12640242

申请日：2009-12-17

Applicant: Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

Inventor： Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

IPC: F01D5/14 ,  F01D9/02

CPC classification number: F01D5/145 ,  F05D2270/172 ,  Y02T50/67 ,  Y02T50/673

Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.

Abstract translation: 翼型件（22）的端壁（25）中的等离子体发生器（48,49,70,71）在方向（50）上引起空气动力学流动，所述方向（50）将端壁边界层的流线（47）改变为流线几何形状（46） 翼型的跨跨区域。 这减少了由边界层的动量缺失产生的旋涡（42），从而提高了空气动力学效率。 等离子体发生器可以围绕前缘以及在燃气涡轮喷嘴结构中的两个翼型件（22）之间排列，并且可以位于由端壁的表面轮廓（66）引起的流线中的校正点（68）处。 等离子体发生器可以被定向以产生与边界层流向量（72）组合的流向量（74），以在减少湍流的方向上产生合成流向量（76）。

公开(公告)号：US07758306B2

公开(公告)日：2010-07-20

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: F01D1/02

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：US20080152505A1

公开(公告)日：2008-06-26

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：US20070059173A1

公开(公告)日：2007-03-15

申请号：US11162434

申请日：2005-09-09

Applicant: Ching-Pang Lee ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Chander Prakash

IPC: F01D5/18

CPC classification number: F01D5/20 ,  F05D2250/712 ,  Y02T50/67

Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil. At least a portion of the pressure-side tip wall is recessed from the pressure sidewall to define an outwardly facing tip shelf, such that the pressure-side tip wall and the tip shelf define a trough therebetween.

Abstract translation: 用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。 翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。 压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。 压力侧顶端壁的至少一部分从压力侧壁凹入以限定向外的顶端架，使得压力侧顶端壁和尖端架在其间限定槽。

公开(公告)号：US20050169752A1

公开(公告)日：2005-08-04

申请号：US10692700

申请日：2003-10-24

Applicant: Ching-Pang Lee ,  Ronald Bunker ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Ronald Bunker ,  Chander Prakash

IPC: F01D5/18 ,  A61B5/04

CPC classification number: F01D5/187 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A turbine airfoil includes pressure and suction sidewalls extending in chord between leading and trailing edges and in span between a root and a tip. A septum is spaced between the sidewalls to define two cooling circuits on opposite sides of the septum which converge between the leading and trailing edges. An array of pins extends inwardly from the pressure sidewall at a discharge end of the circuits, and the pins decrease in length to conform with the converging circuit.

Abstract translation: 涡轮机翼片包括在前缘和后缘之间延伸并且在根部和尖端之间的跨度中的压力和抽吸侧壁。 隔膜间隔开在侧壁之间以在隔膜的相对侧上限定两个冷却回路，其在前缘和后缘之间会聚。 引脚阵列在电路的放电端从压力侧壁向内延伸，并且引脚的长度减小以符合会聚电路。

公开(公告)号：US4120542A

公开(公告)日：1978-10-17

申请号：US750611

申请日：1976-12-15

Applicant: Chander Prakash Bhateja ,  Richard Lassen Alling ,  Dean Edward Johnston

Inventor： Chander Prakash Bhateja ,  Richard Lassen Alling ,  Dean Edward Johnston

IPC: F16C19/30 ,  F16C19/34

CPC classification number: F16C19/30 ,  F16C2240/84

Abstract: The cageless thrust bearing with unguided cylindrical rollers comprises a pair of thrust bearing races with axially separated flat thrust raceways. Cylindrical rollers all having the same diameter are located between the separated flat thrust raceways. The spacing of the rollers is such that the rollers become radially aligned in the bearing under a rotating thrust load, without side or end guidance of the rollers.

Abstract translation: 带无引导圆柱滚子的无笼式推力轴承包括一对带轴向分离的平面推力滚道的推力轴承座圈。 所有具有相同直径的圆柱滚子位于分离的平的推力滚道之间。 辊子的间距使得辊子在旋转的​​推力载荷下在轴承中径向对准，而没有辊的侧向或端部引导。

公开(公告)号：US09810081B2

公开(公告)日：2017-11-07

申请号：US12813658

申请日：2010-06-11

Applicant: Ching-Pang Lee ,  Chander Prakash ,  Reinhard Schilp ,  David A. Little

Inventor： Ching-Pang Lee ,  Chander Prakash ,  Reinhard Schilp ,  David A. Little

IPC: F01D9/02 ,  F23R3/06 ,  F02K1/82 ,  F23R3/00 ,  F23M20/00

CPC classification number: F01D9/023 ,  F02K1/822 ,  F05D2250/13 ,  F05D2250/324 ,  F05D2260/202 ,  F23M20/005 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/00014 ,  F23R2900/03042 ,  Y02T50/675

Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.

公开(公告)号：US09546558B2

公开(公告)日：2017-01-17

申请号：US12832116

申请日：2010-07-08

Applicant: Ching-Pang Lee ,  Danning You ,  Reinhard Schilp ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Danning You ,  Reinhard Schilp ,  Chander Prakash

IPC: F02C7/12 ,  F01D9/02 ,  F23R3/06

CPC classification number: F01D9/023 ,  F02C7/12 ,  F05D2260/96 ,  F23R3/06 ,  F23R2900/00014

Abstract: A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.

Abstract translation: 共振室（42）具有外壁（32），其具有冷却剂入口孔（34A-C），具有声孔（38）的内壁（36）和内壁和外壁之间的侧壁（40A-C） 。 外壁上的凹部（33A-C）具有与外壁的峰（37A-C）相比靠近内壁的底部部分（50）。 冷却剂入口孔可以沿着凹陷的底部部分并且沿着侧壁的底部部分定位，以将冷却剂流（44,41）引向内壁上与声学不对准的冲击位置（43） 孔。 这提高了冲击冷却效率。 外壁的峰（37A-C）在共振室中提供用于目标共振的体积。

公开(公告)号：US20130017095A1

公开(公告)日：2013-01-17

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：US07290986B2

公开(公告)日：2007-11-06

申请号：US11162433

申请日：2005-09-09

Applicant: Mark Edward Stegemiller ,  Chander Prakash ,  Leslie Eugene Leeke ,  Kevin Samuel Klasing ,  Ching-Pang Lee

Inventor： Mark Edward Stegemiller ,  Chander Prakash ,  Leslie Eugene Leeke ,  Kevin Samuel Klasing ,  Ching-Pang Lee

IPC: F01D5/20

CPC classification number: F01D5/20 ,  F05D2250/71 ,  F05D2250/712 ,  Y02T50/67

Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.

Abstract translation: 用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。 翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。 压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。