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公开(公告)号：US20060053800A1
公开(公告)日：2006-03-16
申请号：US10941546
申请日：2004-09-15
Applicant: Robert Orlando , Kattalaicheri Venkataramani , Ching-Pang Lee , Thomas Moniz , Kurt Murrow
Inventor： Robert Orlando , Kattalaicheri Venkataramani , Ching-Pang Lee , Thomas Moniz , Kurt Murrow
IPC: F02C7/12
CPC classification number: F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the compressor, where the core system further includes an intermediate compressor positioned downstream of and in flow communication with the booster compressor, the intermediate compressor being connected to a second drive shaft, and a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; and, a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft. The core system may also include an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid, where the intermediate turbine is utilized to power the second drive shaft. A first source of compressed air having a predetermined pressure is provided to the combustion system inlet and a second source of compressed air having a pressure greater than the first source of compressed air is provided to cool the combustion system.
Abstract translation: 一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于压缩机下游的核心系统，其中所述核心系统还包括位于所述增压压缩机下游并与所述增压压缩机流动连通的中间压缩机，所述中间压缩机连接到第二驱动轴，以及用于产生气体脉冲的燃烧系统 从提供给其入口的流体流增加压力和温度，以便在出口处产生工作流体; 以及低压涡轮机，其位于所述核心系统的下游并与所述核心系统流动连通，所述低压涡轮机用于为所述第一驱动轴提供动力。 核心系统还可以包括位于燃烧系统下游的中间涡轮机，其与工作流体流动连通，其中中间涡轮机用于为第二驱动轴提供动力。 具有预定压力的第一压缩空气源被提供给燃烧系统入口，并且提供具有大于第一压缩空气源的压力的第二压缩空气源以冷却燃烧系统。
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公开(公告)号：US20060051209A1
公开(公告)日：2006-03-09
申请号：US10937642
申请日：2004-09-09
Applicant: Ching-Pang Lee , James Bailey , Nicholas Palmer , Wenfeng Lu
Inventor： Ching-Pang Lee , James Bailey , Nicholas Palmer , Wenfeng Lu
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/20 , F01D11/08 , Y02T50/676
Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges and root and tip. The tip includes squealer ribs extending from a tip floor forming an open tip cavity. The rib along the pressure sidewall has a squared external corner, and a flute extends along the base of the rib at the tip floor.
Abstract translation: 涡轮机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根部和尖端的翼型件。 尖端包括从形成开口尖端腔的尖端底部延伸的尖叫肋。 沿着压力侧壁的肋具有平方的外角，并且凹槽沿尖端底部的肋的基部延伸。
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173.发明申请公开(公告)号：US20060029723A1
公开(公告)日：2006-02-09
申请号：US10714430
申请日：2003-11-13
Applicant: Joseph Rigney , Ching-Pang Lee , Ramgopal Darolia
Inventor： Joseph Rigney , Ching-Pang Lee , Ramgopal Darolia
CPC classification number: B23P6/002 , C23C10/02 , C23C10/60 , C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , C23C28/36 , C25D3/50 , C25D7/00 , C25D7/008 , F05B2230/31 , F05B2230/90 , F05C2253/12
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, and improve upon the prior bond coat 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 applying a β phase NiAl overlay coating to the substrate, and determining the difference in thickness, Δx, between the β phase NiAl overlay coating and the previously removed bond coat. The method further comprises reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt-Δx, 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并改进先前的粘结涂层的方法。 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β相NiAl覆盖涂层施加到基底上，并确定β相NiAl覆盖涂层与先前去除的粘结涂层之间的厚度差异Deltax。 该方法还包括将顶部陶瓷热障涂层重新施加到t + Deltat-Deltax的标称厚度，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。
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公开(公告)号：US06990797B2
公开(公告)日：2006-01-31
申请号：US10656518
申请日：2003-09-05
Applicant: Kattalaicheri Srinivasan Venkataramani , Lawrence Butler , Ching-Pang Lee
IPC: F02C7/0472 , F02K3/04
CPC classification number: F02C7/047 , F05D2260/208 , Y02T50/672 , Y02T50/675
Abstract: A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source, and coupling a second end of the at least one heat pipe in thermal communication with an outer surface of an engine component that is upstream from the heat source.
Abstract translation: 一种方法有利于组装涡轮发动机以便于在发动机运转期间防止在涡轮发动机上的积冰。 该方法包括将至少一个热管耦合到发动机，使得至少一个热管的第一端与热源热连通地联接，并将至少一个热管的第二端与热源连通 发动机部件的外表面，其位于热源的上游。
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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
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。
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Patent Agency Ranking
176.发明申请COATING AND COATING PROCESS INCORPORATING RAISED SURFACE FEATURES FOR AN AIR-COOLED SURFACE 有权包含空气冷却表面的提高表面特性的涂层和涂层工艺公开(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。
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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
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。
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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
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。
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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
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。
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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
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。
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