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：US07870719B2

公开(公告)日：2011-01-18

申请号：US11580788

申请日：2006-10-13

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Scott Michael Carson

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Scott Michael Carson

IPC: F02H1/00

CPC classification number: F01D9/041 ,  F01D5/143 ,  F01D5/145 ,  F05D2260/221 ,  F05D2270/172 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/675

Abstract: A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a conical plasma along the outer duct wall. An exemplary embodiment of the conical plasma generator is mounted to the outer duct wall and including radially inner and outer electrodes separated by a dielectric material. The dielectric material is disposed within a conical groove in a radially inwardly facing surface of the outer duct wall. An AC power supply is connected to the electrodes to supply a high voltage AC potential to the electrodes.

Abstract translation: 等离子体增强的快速扩张的管道系统包括燃气涡轮发动机涡轮机间过渡管道，其具有在管道入口和管道出口之间轴向延伸的径向间隔开的锥形内部和外部管道壁。 锥形等离子体发生器沿着外管道壁产生锥形等离子体。 锥形等离子体发生器的示例性实施例安装到外部管道壁并且包括由电介质材料隔开的径向内部和外部电极。 介电材料设置在外管道壁的径向向内的表面内的锥形槽内。 AC电源连接到电极以向电极提供高电压AC电位。

公开(公告)号：US20100284795A1

公开(公告)日：2010-11-11

申请号：US11966309

申请日：2007-12-28

Applicant: Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

Inventor： Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

IPC: F01D11/08

CPC classification number: F01D11/20 ,  F05D2270/172

Abstract: A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.

Abstract translation: 公开了一种用于压缩机的等离子体泄漏流量控制系统，包括圆周排的压缩机叶片，围绕叶片尖端的环形壳体，位于与叶片的尖端径向分开的位置以及至少一个环形等离子体发生器，其位于环形 套管。 环形等离子体发生器包括由电介质材料隔开的内电极和外电极。 具有等离子体泄漏流量控制系统的燃气涡轮发动机还包括发动机控制系统，其控制环形等离子体发生器的操作，使得可以改变叶片尖端泄漏流。

公开(公告)号：US07785067B2

公开(公告)日：2010-08-31

申请号：US11565229

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D9/04 ,  F01D11/08 ,  F01D11/24 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/314 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49236

Abstract: A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, and coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment.

Abstract translation: 提供一种组装燃气涡轮发动机的方法。 该方法包括联接燃气涡轮发动机内的至少一个涡轮喷嘴段。 至少一个涡轮喷嘴段包括在内带和外带之间延伸的至少一个翼型叶片，其包括后翼缘和径向内表面。 该方法还包括将至少一个涡轮机护罩段联接到至少一个涡轮喷嘴段的下游，其中至少一个涡轮机护罩段包括前缘和径向内表面，并且将冷却流体源与 至少一个涡轮喷嘴段，使得被引导到每个涡轮喷嘴外带后缘的冷却流体朝向至少一个涡轮机护罩段的前缘以倾斜的排出角度引导。

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：US07740444B2

公开(公告)日：2010-06-22

申请号：US11565387

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  James Harvey Laflen ,  Dustin Alfred Placke ,  George Elliott Moore ,  Katherine Jaynetorrence Andersen ,  Daniel Verner Jones

Inventor： Ching-Pang Lee ,  James Harvey Laflen ,  Dustin Alfred Placke ,  George Elliott Moore ,  Katherine Jaynetorrence Andersen ,  Daniel Verner Jones

IPC: F01D25/12

CPC classification number: F01D11/24 ,  F01D25/246 ,  F05D2260/201 ,  F05D2260/205 ,  Y02T50/671 ,  Y02T50/676

Abstract: A method for cooling a turbine shroud assembly includes providing a turbine shroud assembly including a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween. A shroud support circumferentially spans and supports the shroud segment. The shroud support includes a forward hanger coupled to the leading edge, a midsection hanger coupled to the midsection and an aft hanger coupled to the trailing edge. An annular shroud ring structure includes a midsection position control ring coupled to the midsection hanger and an aft position control ring coupled to the aft hanger. Cooling air is extracted from a compressor positioned upstream of the turbine shroud assembly. Cooling air is metered through the shroud support directly into only at least one active convection cooling zone defined between the shroud segment and the shroud support while substantially preventing cooling air from entering an inactive convection cooling zone positioned radially outwardly from the at least one active convection cooling zone and defined between the shroud support and the shroud ring structure and between the midsection position control ring and the aft position control ring.

Abstract translation: 一种用于冷却涡轮机护罩组件的方法包括提供一种涡轮机护罩组件，其包括具有前缘，后缘和在其间限定的中部的护罩段。 护罩支撑件周向地跨越并支撑护罩段。 护罩支撑件包括联接到前缘的前悬挂器，联接到中部的中间吊架和耦合到后缘的后挂架。 环形护罩环结构包括连接到中间悬挂架的中央位置控制环和联接到后悬挂架的后部位置控制环。 从位于涡轮机罩组件上游的压缩机抽出冷却空气。 冷却空气通过护罩支撑件计量直接仅限于限定在护罩区段和护罩支撑件之间的至少一个主动对流冷却区域，同时基本上防止冷却空气进入从至少一个主动对流冷却器径向向外定位的非活动对流冷却区域 并且限定在护罩支撑件和护罩环结构之间以及中间位置控制环和后部位置控制环之间。

公开(公告)号：US20100143139A1

公开(公告)日：2010-06-10

申请号：US12330783

申请日：2008-12-09

Applicant: Vidhu Shekhar Pandey ,  Jeffrey Donald Clements ,  Ching-Pang Lee

Inventor： Vidhu Shekhar Pandey ,  Jeffrey Donald Clements ,  Ching-Pang Lee

IPC: F01D5/22 ,  F01D5/14

CPC classification number: F01D5/145 ,  F01D5/143 ,  Y02T50/673

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20090324422A1

公开(公告)日：2009-12-31

申请号：US11507120

申请日：2006-08-21

Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

IPC: F01D5/18

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.

Abstract translation: 涡轮叶片包括具有沿相对的压力和吸力侧延伸的第一和第二肋的翼型端。 肋从尖端底部向外延伸并且在相对的前缘和后缘处连接在一起。 级联顶端挡板将尖端底部上方的两个肋横向地桥接在尖端的最大宽度的前方，以将端部弦状地分隔成挡板相对侧上的相应的尖端口。

公开(公告)号：US07591070B2

公开(公告)日：2009-09-22

申请号：US11766488

申请日：2007-06-21

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: B23P15/02 ,  F01D5/20

CPC classification number: B23P6/007 ,  F01D5/005 ,  F01D5/20 ,  F05D2260/202 ,  Y10T29/49318 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49728 ,  Y10T29/53091

Abstract: A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge. The first and second sidewalls extending from a root disposed adjacent the dovetail to a tip cap for channeling combustion gases, and a squealer tip including at least one tip rib extending outwardly from the tip cap. The method includes the steps of removing the squealer tip, including the at least one rib tip, from the tip cap and adding new material to the tip cap to serve as a new squealer tip. A plurality of spaced-apart notches is formed in the new material between the leading edge and the trailing edge of the airfoil. At least one hole is formed in each notch communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.

Abstract translation: 具有尖端喷嘴的涡轮机叶片和用于重建用于燃气涡轮发动机的涡轮机叶片的方法。 叶片类型包括具有限定内部空隙并且在前缘和后缘处连接的第一和第二间隔开的侧壁的翼型件。 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用于引导燃烧气体的尖端帽，以及尖叫尖端，其包括从所述尖端帽向外延伸的至少一个尖端肋。 该方法包括以下步骤：从顶盖移除包括至少一个肋尖端的尖叫尖端，并将新材料添加到尖端盖以用作新的尖叫尖端。 在翼缘的前缘和后缘之间的新材料中形成多个间隔开的凹口。 在与翼型件的内部空隙连通的每个凹口中形成至少一个孔，用于从翼型的内部空间引导冷却空气，从而形成尖叫尖端。