公开(公告)号：US07281894B2

公开(公告)日：2007-10-16

申请号：US11162434

申请日：2005-09-09

Applicant: Ching-Pang Lee ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Chander Prakash

IPC: F01D5/20

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：US06790005B2

公开(公告)日：2004-09-14

申请号：US10334091

申请日：2002-12-30

Applicant: Ching-Pang Lee ,  David Glenn Cherry ,  Chander Prakash ,  Aspi Rustom Wadia

Inventor： Ching-Pang Lee ,  David Glenn Cherry ,  Chander Prakash ,  Aspi Rustom Wadia

IPC: F01D516

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/13 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine blade includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The pressure sidewall includes an inclined tip rib offset therein by a ramp defining a tip notch having compound inclinations.

Abstract translation: 燃气涡轮发动机叶片包括在前缘和后缘之间从根部到尖端延伸的压力和吸力侧壁。 压力侧壁包括通过限定具有复合倾斜的尖端凹口的斜面偏置在其中的倾斜尖端肋。

公开(公告)号：US06422821B1

公开(公告)日：2002-07-23

申请号：US09756902

申请日：2001-01-09

Applicant: Ching-Pang Lee ,  Chander Prakash ,  Monty Lee Shelton ,  John Howard Starkweather ,  Hardev Singh ,  Gerard Anthony Rinck

Inventor： Ching-Pang Lee ,  Chander Prakash ,  Monty Lee Shelton ,  John Howard Starkweather ,  Hardev Singh ,  Gerard Anthony Rinck

IPC: F01D518

CPC classification number: F01D5/20 ,  F01D5/186 ,  F05D2240/121 ,  F05D2240/303 ,  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 notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.

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。 在翼型件前缘处的第一和第二尖端壁之间限定了切口。 第二末端壁的至少一部分被凹入以限定尖端架。

公开(公告)号：US5503527A

公开(公告)日：1996-04-02

申请号：US329750

申请日：1994-12-19

Applicant: Ching-Pang Lee ,  Edward F. Pietraszkiewicz ,  Chander Prakash ,  Ronald D. Zerkle

Inventor： Ching-Pang Lee ,  Edward F. Pietraszkiewicz ,  Chander Prakash ,  Ronald D. Zerkle

IPC: F01D5/20 ,  F01D5/18

CPC classification number: F01D5/20 ,  Y02T50/673

Abstract: A gas turbine engine rotor blade includes an airfoil having first and second sidewalls joined together at leading and trailing edges. First and second tip walls extend from adjacent the leading edge along the respective first and second sidewalls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A first notch is disposed in the first tip wall adjacent to the leading edge for channeling into the tip cavity a portion of combustion gases flowable over the airfoil for reducing the heating effect of the gases on the blade tip. In a preferred embodiment, a second notch is disposed adjacent to the trailing edge for promoting flow through the tip cavity from the first notch.

Abstract translation: 燃气涡轮发动机转子叶片包括具有在前缘和后缘处连接在一起的第一和第二侧壁的翼型件。 第一和第二尖端壁沿着相应的第一和第二侧壁的相邻前缘延伸到邻近的后缘并且间隔开以限定其间的尖端腔。 第一凹口设置在与前缘相邻的第一末端壁中，用于将一部分可在翼型上流动的燃烧气体引导到尖端腔中，以减少气体在叶片尖端上的加热效应。 在优选实施例中，第二凹口设置成与后缘相邻，用于促进从第一凹口流过尖端空腔。

公开(公告)号：US5458461A

公开(公告)日：1995-10-17

申请号：US354194

申请日：1994-12-12

Applicant: Ching-Pang Lee ,  Chander Prakash ,  John H. Starkweather ,  Ronald D. Zerkle

Inventor： Ching-Pang Lee ,  Chander Prakash ,  John H. Starkweather ,  Ronald D. Zerkle

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2260/202

Abstract: A wall adapted for use in a gas turbine engine between a first fluid and a second hotter fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends partly inwardly and perpendicularly from the second side toward the first side and is provided with the first fluid through a plurality of longitudinally spaced apart holes. The holes are aligned coplanar with the slot and longitudinally inclined to effect longitudinal overlapping of the first fluid inside the slot prior to discharge therefrom as a substantially continuous film.

Abstract translation: 适于在第一流体和第二热流体之间的燃气涡轮发动机中使用的壁包括可流过第一流体的第一侧和可流动第二流体的相对的第二侧。 细长槽从第二侧向第一侧部分地向内并垂直延伸，并且通过多个纵向间隔开的孔设置有第一流体。 孔与槽对齐并且纵向倾斜以在将槽排出之前的第一流体作为基本上连续的膜进行纵向重叠。

公开(公告)号：US08500404B2

公开(公告)日：2013-08-06

申请号：US12770932

申请日：2010-04-30

Applicant: Matthew D. Montgomery ,  Chander Prakash

Inventor： Matthew D. Montgomery ,  Chander Prakash

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2270/172

Abstract: A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60-61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).

Abstract translation: 一种在组件壁（40）中具有冷却孔（46）的薄膜冷却装置。 壁的第一表面（42）经受热气流（48）。 第二表面（44）接收冷却剂气体（50）。 冷却剂流过孔，然后流过第一表面（42）的下游。 一对或多对配合电极（60-61,62-63,80-81）产生并加速等离子体（70），其产生在促使冷却剂流转向的冷却剂流中的体力加速度（71,82） 围绕冷却孔的入口边缘（57）和/或出口边缘（58），而不与相邻表面（47,42）分离。 电极可以具有将冷却剂扩散到组件壁（40）的热表面（42）上的扇形形状的几何形状。

公开(公告)号：US08435001B2

公开(公告)日：2013-05-07

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: F01D9/00

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：US20110302924A1

公开(公告)日：2011-12-15

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: F02C7/12

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.

Abstract translation: 热燃气通过燃气涡轮发动机的导管。 导管包括具有中心轴线并且限定导管的内部容积以允许热燃气体通过导管的壁结构。 壁结构包括前端，与前端轴向间隔的后端，后端限定用于通过导管的热燃烧气体的燃烧气体出口，以及形成在壁结构中的多个大致径向向外延伸的突起 。 突起各自包括至少一个通过其形成的冷却流体通道，用于允许冷却流体进入内部容积。 突起中的至少一个被成形为使得冷却流体通过它，当它进入内部体积时沿圆周方向发散。

公开(公告)号：US20110268556A1

公开(公告)日：2011-11-03

申请号：US12770932

申请日：2010-04-30

Applicant: Matthew D. Montgomery ,  Chander Prakash

Inventor： Matthew D. Montgomery ,  Chander Prakash

IPC: F04D29/58

CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2270/172

Abstract: A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60-61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).

Abstract translation: 一种在组件壁（40）中具有冷却孔（46）的薄膜冷却装置。 壁的第一表面（42）经受热气流（48）。 第二表面（44）接收冷却剂气体（50）。 冷却剂流过孔，然后流过第一表面（42）的下游。 一对或多对配合电极（60-61,62-63,80-81）产生并加速等离子体（70），其产生在促使冷却剂流转向的冷却剂流中的体力加速度（71,82） 围绕冷却孔的入口边缘（57）和/或出口边缘（58），而不与相邻表面（47,42）分离。 电极可以具有将冷却剂扩散到组件壁（40）的热表面（42）上的扇形形状的几何形状。

公开(公告)号：US06981840B2

公开(公告)日：2006-01-03

申请号：US10692700

申请日：2003-10-24

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

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

IPC: F03D11/00

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。