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51. 发明申请

US20120006028A1 DAMPING RESONATOR WITH IMPINGEMENT COOLING 有权
标题翻译：阻尼谐振器与冲击冷却
公开(公告)号：US20120006028A1
公开(公告)日：2012-01-12
申请号：US12832116
申请日：2010-07-08
申请人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
发明人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
IPC分类号： F02C7/24 , F02C7/12
CPC分类号： F01D9/023 , F02C7/12 , F05D2260/96 , F23R3/06 , F23R2900/00014
摘要： 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.
摘要翻译：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。

52. 发明申请

US20110293434A1 METHOD OF CASTING A COMPONENT HAVING INTERIOR PASSAGEWAYS 有权
标题翻译：铸造具有内部通道的部件的方法
公开(公告)号：US20110293434A1
公开(公告)日：2011-12-01
申请号：US13087428
申请日：2011-04-15
申请人： Ching-Pang Lee , Gary B. Merrill , Andrew J. Burns
发明人： Ching-Pang Lee , Gary B. Merrill , Andrew J. Burns
IPC分类号： F01D5/14 , B32B15/00 , B22D25/02 , B32B3/10 , B22C9/02 , B22C9/10
CPC分类号： B22C9/043 , B22C7/02 , B22C7/026 , B22C9/04 , B22C9/22 , B22D17/00 , B22D29/00 , Y10T428/12361
摘要： A method of casting a component (42) having convoluted interior passageways (44). A desired three dimensional structure corresponding to a later-formed metal alloy component is formed by stacking a plurality of sheets (18, 20) of a fugitive material.The sheets contain void areas (22) corresponding to a desired interior passageway in the metal alloy component. A ceramic slurry material is cast into the three dimensional structure to form either a ceramic core (34) or a complete ceramic casting vessel (38). If just a ceramic core is formed, a wax pattern is formed around the ceramic core and an exterior ceramic shell (38) is formed around the wax pattern by a dipping process prior to the removal of the fugitive material and wax. An alloy component having the desired interior passageway is cast into the casting vessel after the fugitive material is removed.
摘要翻译：一种铸造具有卷曲内部通道（44）的部件（42）的方法。对应于后来形成的金属合金部件的期望的三维结构通过堆叠多个片状物（18,20）而形成。这些板包含对应于金属合金部件中期望的内部通道的空隙区域（22）。将陶瓷浆料材料铸造成三维结构以形成陶瓷芯（34）或完整的陶瓷铸造容器（38）。如果仅形成陶瓷芯，则在陶瓷芯周围形成蜡图案，并且在除去逸散材料和蜡之前通过浸渍工艺在蜡图案周围形成外部陶瓷壳（38）。具有所需内部通道的合金部件在除去逸散材料之后被浇注入铸造容器中。

53. 发明申请

US20110262695A1 Discreetly Defined Porous Wall Structure for Transpirational Cooling 有权
标题翻译：用于旋转冷却的谨慎定义的多孔壁结构
公开(公告)号：US20110262695A1
公开(公告)日：2011-10-27
申请号：US12765004
申请日：2010-04-22
申请人： Ching-Pang Lee , Chander Prakash , Gary B. Merrill , Andreas Heselhaus , Andrew J. Burns
发明人： Ching-Pang Lee , Chander Prakash , Gary B. Merrill , Andreas Heselhaus , Andrew J. Burns
IPC分类号： B32B3/10
CPC分类号： 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
摘要： 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).
摘要翻译：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）。

54. 发明申请

US20110150653A1 Plasma Induced Flow Control of Boundary Layer at Airfoil Endwall 失效
标题翻译：翼型端壁边界层等离子体诱导流量控制
公开(公告)号：US20110150653A1
公开(公告)日：2011-06-23
申请号：US12640242
申请日：2009-12-17
申请人： Matthew D. Montgomery , Ching-Pang Lee , Chander Prakash
发明人： Matthew D. Montgomery , Ching-Pang Lee , Chander Prakash
IPC分类号： F01D5/14 , F01D9/02
CPC分类号： F01D5/145 , F05D2270/172 , Y02T50/67 , Y02T50/673
摘要： 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.
摘要翻译：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）。

55. 发明授权

US07870719B2 Plasma enhanced rapidly expanded gas turbine engine transition duct 有权
标题翻译：等离子体增强了快速扩大的燃气轮机发动机过渡管道
公开(公告)号：US07870719B2
公开(公告)日：2011-01-18
申请号：US11580788
申请日：2006-10-13
申请人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Scott Michael Carson
发明人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Scott Michael Carson
IPC分类号： F02H1/00
CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F05D2260/221 , F05D2270/172 , Y02T50/671 , Y02T50/673 , Y02T50/675
摘要： 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.
摘要翻译：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。

56. 发明申请

US20100284795A1 Plasma Clearance Controlled Compressor 审中-公开
标题翻译：等离子体间隙控制压缩机
公开(公告)号：US20100284795A1
公开(公告)日：2010-11-11
申请号：US11966309
申请日：2007-12-28
申请人： Aspi Rustom Wadia , David Scott Clark , Ching-Pang Lee , Andrew Breeze-Stringfellow , Gregory Scott McNulty
发明人： Aspi Rustom Wadia , David Scott Clark , Ching-Pang Lee , Andrew Breeze-Stringfellow , Gregory Scott McNulty
IPC分类号： F01D11/08
CPC分类号： F01D11/20 , F05D2270/172
摘要： 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.
摘要翻译：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。

57. 发明授权

US07785067B2 Method and system to facilitate cooling turbine engines 有权
标题翻译：便于冷却涡轮发动机的方法和系统
公开(公告)号：US07785067B2
公开(公告)日：2010-08-31
申请号：US11565229
申请日：2006-11-30
申请人： Ching-Pang Lee , Eric Alan Estill , James Harvey Laflen , Paul Hadley Vitt , Michael Elliot Wymore
发明人： Ching-Pang Lee , Eric Alan Estill , James Harvey Laflen , Paul Hadley Vitt , Michael Elliot Wymore
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D9/04 , F01D11/08 , F01D11/24 , F01D25/246 , F05D2240/11 , F05D2240/81 , F05D2250/314 , Y02T50/671 , Y02T50/676 , Y10T29/49236
摘要： 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.
摘要翻译：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。

58. 发明授权

US07758306B2 Turbine assembly for a gas turbine engine and method of manufacturing the same 有权
标题翻译：用于燃气涡轮发动机的涡轮组件及其制造方法
公开(公告)号：US07758306B2
公开(公告)日：2010-07-20
申请号：US11615514
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
IPC分类号： F01D1/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49236
摘要： 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.
摘要翻译：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。

59. 发明授权

US07740444B2 Methods and system for cooling integral turbine shround assemblies 有权
标题翻译：冷却整体涡轮机组件的方法和系统
公开(公告)号：US07740444B2
公开(公告)日：2010-06-22
申请号：US11565387
申请日：2006-11-30
申请人： Ching-Pang Lee , James Harvey Laflen , Dustin Alfred Placke , George Elliott Moore , Katherine Jaynetorrence Andersen , Daniel Verner Jones
发明人： Ching-Pang Lee , James Harvey Laflen , Dustin Alfred Placke , George Elliott Moore , Katherine Jaynetorrence Andersen , Daniel Verner Jones
IPC分类号： F01D25/12
CPC分类号： F01D11/24 , F01D25/246 , F05D2260/201 , F05D2260/205 , Y02T50/671 , Y02T50/676
摘要： 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.
摘要翻译：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。

60. 发明申请

US20100143139A1 BANKED PLATFORM TURBINE BLADE 有权
标题翻译： BANKED平台涡轮叶片
公开(公告)号：US20100143139A1
公开(公告)日：2010-06-10
申请号：US12330783
申请日：2008-12-09
申请人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
发明人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
IPC分类号： F01D5/22 , F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , Y02T50/673
摘要： 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.
摘要翻译：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。

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