公开(公告)号：US20050286998A1

公开(公告)日：2005-12-29

申请号：US10874900

申请日：2004-06-23

Applicant: Ching-Pang Lee ,  Steven Brassfield ,  Ronald Bunker

Inventor： Ching-Pang Lee ,  Steven Brassfield ,  Ronald Bunker

IPC: B23K26/38 ,  F01D5/18 ,  F01D1/00

CPC classification number: B23K26/384

Abstract: A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.

Abstract translation: 燃气涡轮发动机中的壁包括内表面和外表面，其具有穿过其延伸的一排复合人字形薄膜冷却孔。 人字形孔在壁内表面的入口和壁外表面的人字形出口之间纵向和横向分开。

公开(公告)号：US20050271514A1

公开(公告)日：2005-12-08

申请号：US10906903

申请日：2005-03-11

Applicant: Ching-Pang Lee ,  Robert Schafrik ,  Ramgopal Darolia ,  Joseph Rigney

Inventor： Ching-Pang Lee ,  Robert Schafrik ,  Ramgopal Darolia ,  Joseph Rigney

IPC: B32B15/16 ,  C08F2/48 ,  C23C4/02 ,  C23C4/08 ,  C23C14/02 ,  C23C14/04 ,  C23C14/16 ,  C23C16/06 ,  C23C28/00 ,  F23M5/00 ,  F23R3/00 ,  F28F13/18

CPC classification number: C23C4/02 ,  C23C4/073 ,  C23C4/08 ,  C23C14/025 ,  C23C14/044 ,  C23C14/16 ,  C23C28/021 ,  C23C28/022 ,  F05B2240/11 ,  F05B2250/60 ,  F05B2260/224 ,  F05C2253/12 ,  F23M5/00 ,  F23M2900/05004 ,  F23R3/002 ,  F28F13/18 ,  F28F13/185 ,  Y10T428/12063 ,  Y10T428/12493 ,  Y10T428/12639 ,  Y10T428/12646 ,  Y10T428/12931 ,  Y10T428/12944 ,  Y10T428/12993

Abstract: A coating and coating process for incorporating surface features on an air-cooled substrate surface of a component for the purpose of promoting heat transfer from the component. The coating process generally comprises depositing a first metallic coating material on the surface of the component using a first set of coating conditions to form a first environmental coating layer, and then depositing a second metallic coating material using a second set of coating conditions that differ from the first set, such that an outer environmental coating layer is formed having raised surface features that cause the surface of the outer environmental coating layer to be rougher than the surface of the first environmental coating layer.

Abstract translation: 用于将部件的空气冷却基板表面上的表面特征引入到涂层和涂覆方法中，以促进从部件的热传递。 涂覆方法通常包括使用第一组涂覆条件在组件的表面上沉积第一金属涂层材料以形成第一环境涂层，然后使用第二组涂覆条件沉积第二金属涂层材料 第一组，使得外部环境涂层形成具有使外部环境涂层的表面比第一环境涂层的表面更粗糙的凸起表面特征。

公开(公告)号：US06960060B2

公开(公告)日：2005-11-01

申请号：US10718462

申请日：2003-11-20

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/08 ,  F01D5/14 ,  F01D5/18 ,  F01D5/20 ,  F01D11/02 ,  F02C7/18 ,  F04D29/38

CPC classification number: F01D5/187 ,  F01D5/081 ,  F01D5/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes a hollow airfoil joined to a dovetail and platform. The airfoil includes leading and trailing edge cooling circuits disposed between the opposite pressure and suction sidewalls of the airfoil along the leading and trailing edges thereof. The leading edge cooling circuit includes a radial inlet commencing in the base of the dovetail, and the trailing edge cooling circuit includes an axial inlet commencing in the aft face of the dovetail for receiving coolant having different pressure and temperature.

Abstract translation: 涡轮叶片包括连接到燕尾和平台的中空翼型件。 翼型件包括沿翼缘的前缘和后缘设置在翼型的相对的压力和吸力侧壁之间的前缘和后缘冷却回路。 前缘冷却回路包括从燕尾榫的底部开始的径向入口，后缘冷却回路包括从燕尾榫的后表面开始接收具有不同压力和温度的冷却剂的轴向入口。

公开(公告)号：US20050226726A1

公开(公告)日：2005-10-13

申请号：US10820325

申请日：2004-04-08

Applicant: Ching-Pang Lee ,  Aspi Wadia ,  David Cherry

Inventor： Ching-Pang Lee ,  Aspi Wadia ,  David Cherry

IPC: F01D5/18 ,  B63H1/14

CPC classification number: F01D5/187 ,  Y02T50/676

Abstract: A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality of independent cooling circuits are disposed inside the airfoil correspondingly along the pressure and suction sidewalls thereof. Each circuit includes an inlet channel extending through the dovetail. One of the circuits includes multiple longitudinal channels separated by corresponding perforate partitions each including a row of impingement holes for cascade impingement cooling the inner surface of the airfoil.

Abstract translation: 涡轮机叶片包括具有相对的压力和抽吸侧壁的翼型件，其在相对的前缘和后缘处连接在一起并且从根部到尖端纵向延伸。 多个独立的冷却回路相应地沿其压力和吸力侧壁设置在翼型内。 每个电路包括延伸穿过燕尾榫的入口通道。 电路中的一个包括由对应的穿孔隔板分开的多个纵向通道，每个隔板包括一排冲击孔，用于级联冲击冷却翼型件的内表面。

公开(公告)号：US06931858B2

公开(公告)日：2005-08-23

申请号：US10422314

申请日：2003-04-24

Applicant: Kattalaicheri Srinivasan Venkataramani ,  Lawrence Butler ,  Ching-Pang Lee ,  Harvey Michael Maclin

Inventor： Kattalaicheri Srinivasan Venkataramani ,  Lawrence Butler ,  Ching-Pang Lee ,  Harvey Michael Maclin

IPC: F02C5/04 ,  F02C5/11 ,  F02C5/12 ,  F02K3/06 ,  F02K7/06 ,  F02K7/075 ,  F23R7/00

CPC classification number: F02K3/06 ,  F02C5/11 ,  F02C5/12 ,  F02K7/02 ,  F05D2250/314 ,  F23R7/00

Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where a plurality of spaced detonation passages are disposed therethrough. Each detonation passage includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases exit the aft surface of the cylindrical member to create a torque which causes the cylindrical member to rotate. Each detonation passage further includes a first end located adjacent the forward surface of the cylindrical member and a second end located adjacent the aft surface of the cylindrical member.

Abstract translation: 用于具有延伸穿过其中的纵向中心线轴的燃气涡轮发动机的脉冲爆震系统包括具有前表面，后表面和外周表面的可旋转圆柱形构件，其中多个间隔开的爆震通道穿过其中。 每个爆震通道包括至少一个具有延伸穿过的纵向轴线的部分，该纵向轴线以与纵向中心线轴线成圆周方向定位。 脉冲爆震系统还包括可旋转地连接到圆柱形构件的轴和定子，其与圆柱形构件的前表面和轴的一部分间隔开地配置。 定子具有至少一组端口，当圆柱形构件旋转时，该组端口可与引爆通道对准。 以这种方式，在引爆通道中进行爆震循环，使得燃烧气体离开圆柱形构件的后表面以产生使圆柱形构件旋转的扭矩。 每个引爆通道还包括位于圆柱形构件的前表面附近的第一端和位于圆柱形构件的后表面附近的第二端。

公开(公告)号：US20050169752A1

公开(公告)日：2005-08-04

申请号：US10692700

申请日：2003-10-24

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

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

IPC: F01D5/18 ,  A61B5/04

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：US20050111964A1

公开(公告)日：2005-05-26

申请号：US10718149

申请日：2003-11-20

Applicant: Erich Krammer ,  Richard Haubert ,  Ching-Pang Lee ,  Harvey Maclin

Inventor： Erich Krammer ,  Richard Haubert ,  Ching-Pang Lee ,  Harvey Maclin

IPC: F01D5/08 ,  F01D9/02 ,  F01D11/02 ,  F01D25/12 ,  F02C3/067 ,  F02C6/08 ,  F02C7/12 ,  F02C7/18 ,  F02C7/28 ,  F02C9/22 ,  F16J15/447 ,  F01D5/14

CPC classification number: F01D25/12 ,  F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F02C7/18 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbofan engine includes in serial flow communication a first fan, second fan, multistage compressor, combustor, first turbine, second turbine, and third turbine. The first turbine is joined to the compressor by a first shaft. The second turbine is joined to the second fan by a second shaft. And, the third turbine is joined to the first fan by a third shaft. First, second, and third cooling circuits are joined to different stages of the compressor for cooling the forward and aft sides and center bore of the first turbine with different pressure air.

Abstract translation: 涡轮风扇发动机包括串联流动连通的第一风扇，第二风扇，多级压缩机，燃烧器，第一涡轮机，第二涡轮机和第三涡轮机。 第一涡轮机通过第一轴连接到压缩机。 第二涡轮机通过第二轴连接到第二风扇。 并且，第三涡轮机通过第三轴接合到第一风扇。 第一，第二和第三冷却回路连接到压缩机的不同阶段，用不同的压力空气冷却第一涡轮机的前后侧和中心孔。

公开(公告)号：US20050106316A1

公开(公告)日：2005-05-19

申请号：US10714213

申请日：2003-11-13

Applicant: Joseph Rigney ,  Ching-Pang Lee ,  Ramgopal Darolia

Inventor： Joseph Rigney ,  Ching-Pang Lee ,  Ramgopal Darolia

IPC: B23P6/00 ,  C23C26/00 ,  C23C28/00 ,  F01D5/00 ,  F01D5/14 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00 ,  B32B35/00

CPC classification number: C23C28/321 ,  C23C26/00 ,  C23C28/325 ,  C23C28/3455 ,  F01D5/005 ,  F01D5/288 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/501 ,  Y10T29/49318

Abstract: According to an embodiment of the invention, a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade, is disclosed. The method comprises providing an engine run high pressure turbine blade including a base metal substrate made of a nickel-based alloy and having thereon a thermal barrier coating system. The thermal barrier coating system comprises a diffusion bond coat on the base metal substrate and a top ceramic thermal barrier coating comprising a yttria stabilized zirconia material. The top ceramic thermal barrier coating has a nominal thickness t. The method further comprises removing the thermal barrier coating system, wherein a portion of the base metal substrate also is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness, Δt. The method also comprises reapplying the diffusion bond coat to the substrate, wherein the bond coat is reapplied to a thickness, which is about the same as applied prior to the engine operation; and reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt, wherein Δt compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.

Abstract translation: 根据本发明的实施例，公开了一种已经暴露于发动机操作的用于修复涂覆的高压涡轮机叶片以恢复叶片的被覆翼型轮廓尺寸的方法。 该方法包括提供一种发动机运行的高压涡轮叶片，其包括由镍基合金制成的基底金属基底并且具有热障涂层系统。 热障涂层系统包括在基底金属基底上的扩散粘合涂层和包含氧化钇稳定的氧化锆材料的顶部陶瓷热障涂层。 顶部陶瓷热障涂层具有标称厚度t。 该方法还包括去除热障涂层系统，其中基底金属衬底的一部分也被去除，并且确定移除的母体金属衬底的厚度。 去除的贱金属基材的部分厚度为Deltat。 该方法还包括将扩散粘合涂层重新施加到基底上，其中粘结涂层重新施加到与发动机操作前相同的厚度; 并将顶部陶瓷热障涂层重新施加到标称厚度t + Deltat，其中Deltat补偿去除的基底金属基底的部分。 有利地，高压涡轮机叶片的被覆翼型轮廓尺寸恢复到发动机运行之前的涂层尺寸。

公开(公告)号：US20050106021A1

公开(公告)日：2005-05-19

申请号：US10720045

申请日：2003-11-19

Applicant: Ronald Bunker ,  Jeremy Bailey ,  Ching-Pang Lee

Inventor： Ronald Bunker ,  Jeremy Bailey ,  Ching-Pang Lee

IPC: F01D9/02 ,  F01D5/18 ,  F02C7/18 ,  F28F3/02 ,  F28F3/04 ,  F28F13/12 ,  B63H1/14

CPC classification number: F28F13/12 ,  F01D5/187 ,  F05D2230/90 ,  F05D2250/28 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  F28F3/022 ,  F28F3/044 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/4932

Abstract: A component includes at least one wall having an inner portion and an outer portion. A number of pins extend between the inner and outer portions of the wall. The pins define a mesh cooling arrangement having a number of flow channels. A number of dimples are located in at least one of the inner and outer portions of the wall. The component may also include a number of turbulators disposed on at least one of the inner and outer portions of the wall.

Abstract translation: 一个部件包括至少一个具有内部部分和外部部分的壁。 多个销在壁的内部和外部之间延伸。 销钉限定具有多个流动通道的网状冷却装置。 多个凹坑位于壁的内部和外部的至少一个中。 该部件还可以包括设置在壁的内部和外部部分中的至少一个上的多个紊流器。

公开(公告)号：US06617003B1

公开(公告)日：2003-09-09

申请号：US09707023

申请日：2000-11-06

Applicant: Ching-Pang Lee ,  Robert Edward Schafrik ,  Ramgopal Darolia

Inventor： Ching-Pang Lee ,  Robert Edward Schafrik ,  Ramgopal Darolia

IPC: B32B1504

CPC classification number: C23C28/3215 ,  C23C28/321 ,  C23C28/325 ,  C23C28/3455 ,  F01D5/182 ,  F01D5/187 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12611 ,  Y10T428/12736 ,  Y10T428/12944 ,  Y10T428/24273 ,  Y10T428/24289 ,  Y10T428/24298 ,  Y10T428/24306

Abstract: An actively cooled TBC bond coat wherein active convection cooling is provided through micro channels inside or adjacent to a bond coat layer applied to a substrate. The micro channels communicate directly with at least one cooling fluid supply contained within a turbine engine component, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate is covered with an actively cooled bond coat layer, it will reduce the cooling requirement for the substrate, thus allowing the engine to run at higher operating temperature without the need for additional cooling air, achieving a better engine performance. In one form, the component includes a substrate having at least one substrate channel with a first and second end. At least one micro channel is in fluid communication with a plenum which in turn is in fluid communication with at least one substrate channel through an exit orifice in the substrate channel which is at a first end of the substrate channel. A second end of the substrate channel is in communication with a cooling fluid supply, for example, cooling circuits contained within the turbine engine component. The micro channel is located between the substrate surface and the outer gas flow path surface of the component.

Abstract translation: 主动冷却的TBC粘合涂层，其中主动对流冷却通过施加到基底的粘合涂层的内部或附近的微通道提供。 微通道与包含在涡轮发动机部件内的至少一个冷却流体供应件直接连通，从而为粘合涂层提供直接和有效的冷却。 由于衬底被主动冷却的粘合涂层覆盖，所以它将降低衬底的冷却要求，从而允许发动机在更高的工作温度下运行，而不需要额外的冷却空气，实现更好的发动机性能。 在一种形式中，组件包括具有至少一个具有第一和第二端的衬底通道的衬底。 至少一个微通道与气室流体连通，该气室又与通过基板通道中位于衬底通道的第一端处的出口孔与至少一个衬底通道流体连通。 衬底通道的第二端与冷却流体供应源连通，例如包含在涡轮发动机部件内的冷却回路。 微通道位于基板表面和部件的外部气体流动通道表面之间。