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。

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：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。

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：US09206904B2

公开(公告)日：2015-12-08

申请号：US12832141

申请日：2010-07-08

Applicant: Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

Inventor： Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

IPC: F16J15/32 ,  F01D11/02

CPC classification number: F16J15/3292 ,  F01D11/02 ,  F05D2240/57

Abstract: A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.

Abstract translation: 一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。 密封构件包括多个柔性密封条。 每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的 轴。 密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

公开(公告)号：US20120006028A1

公开(公告)日：2012-01-12

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: F02C7/24 ,  F02C7/12

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）具有与外壁的顶部（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：US20110262695A1

公开(公告)日：2011-10-27

申请号：US12765004

申请日：2010-04-22

Applicant: Ching-Pang Lee ,  Chander Prakash ,  Gary B. Merrill ,  Andreas Heselhaus ,  Andrew J. Burns

Inventor： Ching-Pang Lee ,  Chander Prakash ,  Gary B. Merrill ,  Andreas Heselhaus ,  Andrew J. Burns

IPC: B32B3/10

CPC classification number: F01D5/182 ,  B33Y80/00 ,  F01D5/183 ,  F01D5/184 ,  F05D2230/22 ,  F05D2230/90 ,  F05D2250/18 ,  F05D2250/185 ,  F05D2250/28 ,  F05D2250/30 ,  F05D2260/203 ,  F05D2260/221 ,  Y10T428/24273

Abstract: A wall structure (32, 42, 68, 70, 80) with layers (A, B, C, D, E) of non-random voids (26A, 26B, 28B, 30B) that interconnect to form discretely defined tortuous passages between an interior (21) and an exterior surface (23) of the wall for transpiration cooling of the wall. A coolant flow (38) through the wall may be metered by restrictions in coolant outlets (31) and/or within the passages to minimize the coolant requirement. Pockets (44) may be formed on the exterior surface of the wall for thermal Insulation (46). The layers may be formed by lamination, additive manufacturing, or casting. Layer geometries include alternating layers (A, B, C) with different overlapping void patterns (42), 3-D lattice structures (70), and offset waffle structures (80).

Abstract translation: 具有非随机空隙（26A，26B，28B，30B）的层（A，B，C，D，E）的壁结构（32,42,68,70,80），其互连以在 所述壁的内部（21）和外表面（23）用于所述壁的蒸发冷却。 通过壁的冷却剂流（38）可以通过冷却剂出口（31）和/或通道内的限制来计量，以使冷却剂需求最小化。 口袋（44）可以形成在隔热壁的外表面上（46）。 层可以通过层压，添加剂制造或铸造形成。 层几何形状包括具有不同重叠空白图案（42），3-D网格结构（70）和偏置华夫饼结构（80）的交替层（A，B，C）。

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。