公开(公告)号：US20080145233A1

公开(公告)日：2008-06-19

申请号：US11639878

申请日：2006-12-15

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: F01D5/12 ,  F01D17/00

CPC classification number: F01D5/147 ,  F01D5/145 ,  F01D9/041 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2270/172 ,  Y02T50/673 ,  Y10S415/914

Abstract: A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on an outer wall of the airfoil with first and second pluralities of the plasma generators on pressure and suction sides of the airfoil respectively. The plasma generators may include inner and outer electrodes separated by a dielectric material disposed within a grooves in an outer hot surface of the outer wall of the airfoil. The plasma generators may be located at an aft end of the airfoil and the inner electrodes flush with the trailing edge base. A method for operating the system includes energizing one or more of plasma generators in steady state or unsteady modes.

Abstract translation: 后缘涡流减少系统包括在翼展方向上延伸的燃气涡轮发动机翼型件，在翼型件的后缘周围的后缘区域中的一个或多个翼展方向延伸的等离子体发生器。 等离子体发生器可以分别安装在机翼的外壁上，其中第一和第二多个等离子体发生器分别在翼型的压力和吸力侧。 等离子体发生器可以包括由设置在翼型件的外壁的外部热表面中的凹槽内的介电材料隔开的内部和外部电极。 等离子体发生器可以位于翼型的后端，并且内部电极与后缘基座齐平。 用于操作该系统的方法包括给稳态或不稳定模式中的一个或多个等离子体发生器通电。

公开(公告)号：US20080145210A1

公开(公告)日：2008-06-19

申请号：US11639876

申请日：2006-12-15

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: F01D5/18

CPC classification number: F01D5/145 ,  F01D5/143 ,  F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F04D29/681 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/202 ,  F05D2270/17 ,  F05D2270/172 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S415/914

Abstract: A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.

Abstract translation: 前缘涡流减少系统包括沿翼展方向远离端壁延伸的燃气涡轮发动机翼型件，一个或多个等离子体发生器，其在翼展方向上延伸通过翼型件和端壁之间的圆角， 围绕机翼的前缘，靠近圆角。 等离子体发生器可操作用于产生在前缘区域中的圆角的一部分上延伸的等离子体。 等离子体发生器可以安装在翼型件的外壁上，其中等离子体发生器的第一部分在翼型的压力侧，等离子体发生器的第二部分在翼型的吸力侧。 用于操作该系统的方法包括激励一个或多个等离子体发生器以形成处于稳定状态或不稳定模式的等离子体。

公开(公告)号：US07387488B2

公开(公告)日：2008-06-17

申请号：US11161500

申请日：2005-08-05

Applicant: Glenn Herbert Nichols ,  Kurt Grover Brink ,  Ching-Pang Lee

Inventor： Glenn Herbert Nichols ,  Kurt Grover Brink ,  Ching-Pang Lee

IPC: F03B11/00

CPC classification number: F01D9/04 ,  F01D5/288 ,  F01D11/08 ,  F01D11/24 ,  F01D25/12 ,  F01D25/246 ,  F05D2230/90 ,  F05D2240/11

Abstract: A cooled turbine shroud includes an arcuate flow path surface adapted to surround a row of rotating turbine blades, and an opposed interior surface; a forward overhang defining an axially-facing leading edge, an outwardly-extending forward wall and an outwardly-extending aft wall; opposed first and second sidewalls, wherein the forward and aft walls and the sidewalls define an open shroud plenum; at least one leading edge cooling hole extending from the shroud plenum to the leading edge; and at least one sidewall cooling hole extending from the plenum to one of the sidewalls. The flow path surface is free of cooling holes and may include a protective coating applied thereto.

Abstract translation: 冷却的涡轮机护罩包括适于围绕一排旋转涡轮叶片的弧形流动路径表面和相对的内表面; 向前突出部，其限定面向前的前缘，向外延伸的前壁和向外延伸的后壁; 相对的第一和第二侧壁，其中前壁和后壁以及侧壁限定开放的护罩增压室; 至少一个前缘冷却孔从护罩增压室延伸到前缘; 以及至少一个侧壁冷却孔，其从所述增压室延伸到所述侧壁之一。 流路表面没有冷却孔，并且可以包括施加到其上的保护涂层。

公开(公告)号：US20080131262A1

公开(公告)日：2008-06-05

申请号：US11565447

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Verner Jones

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Verner Jones

IPC: F01D5/08 ,  F01D25/12

CPC classification number: F01D9/04 ,  F05D2240/80 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R2900/03044 ,  Y02T50/671 ,  Y02T50/676

Abstract: A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip to facilitate film cooling the shroud segment.

Abstract translation: 一种用于冷却燃气涡轮发动机的护罩区段的方法包括提供一种涡轮机护罩组件，其包括具有限定前表面的前缘的护罩区段。 涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的前表面和前表面之间限定间隙，其中形成在后表面上的唇缘相对于间隙径向向内定位 并且从所述间隙基本轴向地延伸到下游。 冷却空气被引导到间隙中。 离开间隙的冷却空气撞击唇缘，以便薄膜冷却护罩段。

公开(公告)号：US07374401B2

公开(公告)日：2008-05-20

申请号：US11069869

申请日：2005-03-01

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/18 ,  F05D2200/24 ,  F05D2250/20 ,  F05D2250/26 ,  F05D2250/292 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine airfoil a plurality of cooling holes formed in the external surface of the airfoil in fluid communication with a cooling circuit. The cooling holes have a metering section and a diffuser section opening to the external surface of the airfoil. The diffuser section has top, bottom and opposed side walls, where at least the opposed side walls and one or the other of the top and bottom walls of the diffuser section have a downstream diverging, bell-shaped configuration for achieving a flow of the cooling film from the cooling circuit with enhanced spread, enhanced attachment and less turbulence to a downstream surface of the airfoil local to each respective cooling hole.

Abstract translation: 涡轮机翼型件形成在与冷却回路流体连通的翼型件的外表面中的多个冷却孔。 冷却孔具有通向翼型件的外表面的计量部分和扩散部分。 扩散器部分具有顶部，底部和相对的侧壁，其中至少相对的侧壁和扩散器部分的顶壁和底壁中的一个或另一个具有下游发散的钟形构造，用于实现冷却 来自冷却回路的膜具有增强的扩散，增强的附着和较少的湍流到局部于每个相应的冷却孔的翼型的下游表面。

公开(公告)号：US20080112794A1

公开(公告)日：2008-05-15

申请号：US11595669

申请日：2006-11-10

Applicant: Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

Inventor： Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

IPC: F01D1/00

CPC classification number: F02C7/12 ,  F01D5/189 ,  F05D2220/3212 ,  F05D2260/201 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.

Abstract translation: 燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。 涡轮机包括喷嘴，随后是一排转子叶片。 第一泄放回路在压缩机的最后阶段和喷嘴的叶片中的前冷却通道之间流动连通地连接，用于在第一压力下用加压的一次空气向其中供给第一冷却孔。 第二泄放回路在压缩机的中间级与喷嘴叶片中的后冷却通道之间流动连通地连接，以在小于第一压力的第二压力下用加压的二次空气供给第二冷却孔。

公开(公告)号：US07360988B2

公开(公告)日：2008-04-22

申请号：US11297672

申请日：2005-12-08

Applicant: Ching-Pang Lee ,  Wenfeng Lu ,  Douglas Marti Fortuna ,  Jakub Roniewicz ,  Robert Andrzej Gniazdowski

Inventor： Ching-Pang Lee ,  Wenfeng Lu ,  Douglas Marti Fortuna ,  Jakub Roniewicz ,  Robert Andrzej Gniazdowski

IPC: F01D25/14

CPC classification number: F01D9/00 ,  F01D25/243 ,  Y10T29/49323

Abstract: A method facilitates the assembly of a gas turbine engine. The method comprises providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands, wherein the vane includes a first sidewall and a second sidewall connected together at a leading edge and a trailing edge and coupling the turbine nozzle to a combustor that includes a plurality of circumferentially-spaced cooling openings that are oriented with respect to the turbine nozzle such that cooling air discharged therefrom during engine operation is biased towards the vane leading edge.

Abstract translation: 一种方法有助于燃气涡轮发动机的组装。 该方法包括提供包括内带，外带和在内带和外带之间延伸的至少一个叶片的涡轮喷嘴，其中叶片包括在前缘连接在一起的第一侧壁和第二侧壁， 以及将所述涡轮喷嘴耦合到燃烧器，所述燃烧器包括相对于所述涡轮喷嘴定向的多个周向间隔开的冷却开口，使得在发动机操作期间从其排出的冷却空气朝向所述叶片前缘偏置。

公开(公告)号：US20080000610A1

公开(公告)日：2008-01-03

申请号：US11855709

申请日：2007-09-14

Applicant: Ronald Bunker ,  Canan Hardwicke ,  Ching-Pang Lee

Inventor： Ronald Bunker ,  Canan Hardwicke ,  Ching-Pang Lee

IPC: B22C7/06 ,  B22D29/00

CPC classification number: B22C9/10 ,  B33Y10/00 ,  C04B41/009 ,  C04B41/5031 ,  C04B41/87 ,  C04B2111/0087 ,  C23C4/01 ,  F05B2260/222 ,  C04B41/4539 ,  C04B41/4572 ,  C04B41/5029 ,  C04B35/04 ,  C04B35/10 ,  C04B35/14 ,  C04B35/18 ,  C04B35/565 ,  C04B35/48 ,  C04B35/584 ,  C04B35/481 ,  C04B35/505

Abstract: A method of forming at least one concavity of a selected size and shape within a surface of an internal passageway of a metallic component comprises: depositing a ceramic-based material by a direct-write technique onto a ceramic core which is suitable for forming the internal passageway during a casting process to form the metallic component, wherein the ceramic-based material is deposited as a positive feature; heat-treating the deposited ceramic-based material; forming the metallic component by a casting process in which the ceramic core is incorporated into the casting, in a position selected as a desired position for the internal passageway; and then removing the ceramic core from the metal component after the casting process is complete, thereby forming the internal passageway, with the concavity contained within the surface of the passageway, said concavity formed by removal of the positive feature of the ceramic-based material.

Abstract translation: 在金属部件的内部通道的表面内形成选定尺寸和形状的至少一个凹部的方法包括：通过直接写入技术将陶瓷基材料沉积到适于形成内部的陶瓷芯上 在铸造过程中形成金属部件的通道，其中所述陶瓷基材料作为阳性特征沉积; 对沉积的陶瓷基材料进行热处理; 通过铸造工艺形成金属部件，其中将陶瓷芯体结合到铸件中，位于被选择为内部通道的期望位置的位置; 然后在铸造过程完成之后从金属部件上除去陶瓷芯，由此形成内部通道，凹部包含在通道的表面内，通过去除陶瓷基材料的积极特征而形成所述凹部。

公开(公告)号：US07302990B2

公开(公告)日：2007-12-04

申请号：US10841366

申请日：2004-05-06

Applicant: Ronald Scott Bunker ,  Canan Uslu Hardwicke ,  Ching-Pang Lee

Inventor： Ronald Scott Bunker ,  Canan Uslu Hardwicke ,  Ching-Pang Lee

IPC: B22C9/00

CPC classification number: B22C9/10 ,  B33Y10/00 ,  C04B41/009 ,  C04B41/5031 ,  C04B41/87 ,  C04B2111/0087 ,  C23C4/01 ,  F05B2260/222 ,  C04B41/4539 ,  C04B41/4572 ,  C04B41/5029 ,  C04B35/04 ,  C04B35/10 ,  C04B35/14 ,  C04B35/18 ,  C04B35/565 ,  C04B35/48 ,  C04B35/584 ,  C04B35/481 ,  C04B35/505

Abstract: A method of forming at least one concavity of a selected size and shape within a surface of an internal passageway of a metallic component comprises: depositing a ceramic-based material by a direct-write technique onto a ceramic core which is suitable for forming the internal passageway during a casting process to form the metallic component, wherein the ceramic-based material is deposited as a positive feature; heat-treating the deposited ceramic-based material; forming the metallic component by a casting process in which the ceramic core is incorporated into the casting, in a position selected as a desired position for the internal passageway; and then removing the ceramic core from the metal component after the casting process is complete, thereby forming the internal passageway, with the concavity contained within the surface of the passageway, said concavity formed by removal of the positive feature of the ceramic-based material.

Abstract translation: 在金属部件的内部通道的表面内形成选定尺寸和形状的至少一个凹部的方法包括：通过直接写入技术将陶瓷基材料沉积到适于形成内部的陶瓷芯上 在铸造过程中形成金属部件的通道，其中所述陶瓷基材料作为阳性特征沉积; 对沉积的陶瓷基材料进行热处理; 通过铸造工艺形成金属部件，其中将陶瓷芯体结合到铸件中，位于被选择为内部通道的期望位置的位置; 然后在铸造过程完成之后从金属部件上除去陶瓷芯，由此形成内部通道，凹部包含在通道的表面内，通过去除陶瓷基材料的积极特征而形成所述凹部。

公开(公告)号：US07293961B2

公开(公告)日：2007-11-13

申请号：US11294218

申请日：2005-12-05

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  Steven Robert Brassfield

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  Steven Robert Brassfield

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/185 ,  F05D2260/201 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine airfoil includes pressure and suction sidewalls spaced apart to define flow channels extending in span and separated by ribs. Side channels are disposed along one sidewall and spaced from the opposite sidewall by the ribs, and a mid channel bridges the sidewalls. The side and mid channels are arranged in a zigzag serpentine cooling circuit alternating therebetween for transferring heat from the sidewall into the mid channel.

Abstract translation: 涡轮机翼片包括间隔开的压力和抽吸侧壁，以限定在跨度中延伸并由肋分隔的流动通道。 侧通道沿着一个侧壁设置并且通过肋与相对侧壁间隔开，并且中间通道桥接侧壁。 侧通道和中间通道以锯齿形蛇形冷却回路布置，用于将热量从侧壁传送到中间通道。