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61. 发明申请

US20070031245A1 Thermally compliant C-clip 有权
标题翻译：耐热兼容的C形夹
公开(公告)号：US20070031245A1
公开(公告)日：2007-02-08
申请号：US11161518
申请日：2005-08-06
申请人： Michael Ruthemeyer , Glenn Nichols , Ching-Pang Lee
发明人： Michael Ruthemeyer , Glenn Nichols , Ching-Pang Lee
IPC分类号： F01D25/26
CPC分类号： F01D9/04 , F05D2230/60 , F05D2240/11 , F05D2260/30 , F05D2260/941
摘要： A C-clip for a gas turbine engine includes an arcuate outer arm having a first radius of curvature; an arcuate, inner arm having a second radius of curvature which is substantially greater than the first radius of curvature; and an arcuate extending flange connecting the outer and inner arms. The flange, the outer arm, and the inner arm collectively define a generally C-shaped cross-section. A shroud assembly includes a shroud segment with a mounting flange, and a shroud hanger with an arcuate hook disposed in mating relationship to the mounting flange. An arcuate C-clip having inner and outer arms overlaps the hook and the mounting flange. The shroud segment and the C-clip are subject to thermal expansion at the hot operating condition. A dimension of one of the shroud segment and the C-clip are selected to produce a preselected dimensional relationship therebetween at the hot operating condition.
摘要翻译：用于燃气涡轮发动机的C形夹包括具有第一曲率半径的弓形外臂; 具有第二曲率半径的弓形内臂，其基本上大于所述第一曲率半径; 以及连接外臂和内臂的弓形延伸法兰。凸缘，外臂和内臂共同地限定了大致C形的横截面。护罩组件包括具有安装凸缘的护罩段和具有与安装法兰配合关系设置的弓形钩的护罩。具有内臂和外臂的弧形C形夹与钩和安装法兰重叠。护罩段和C形夹在热操作条件下经受热膨胀。选择护罩段和C形夹之一的尺寸以在热操作条件下产生预定尺寸关系。

62. 发明授权

US07118342B2 Fluted tip turbine blade 有权
公开(公告)号：US07118342B2
公开(公告)日：2006-10-10
申请号：US10937642
申请日：2004-09-09
申请人： Ching-Pang Lee , James Robert Bailey , Nicholas Charles Palmer , Wenfeng Lu
发明人： Ching-Pang Lee , James Robert Bailey , Nicholas Charles Palmer , Wenfeng Lu
IPC分类号： F01D5/14
CPC分类号： F01D5/186 , F01D5/20 , F01D11/08 , Y02T50/676
摘要： 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.

63. 发明授权

US07094444B2 Method for repairing coated components using NiAl bond coats 有权
标题翻译：使用NiAl粘合涂层修复涂层部件的方法
公开(公告)号：US07094444B2
公开(公告)日：2006-08-22
申请号：US10714430
申请日：2003-11-13
申请人： Joseph D. Rigney , Ching-Pang Lee , Ramgopal Darolia
发明人： Joseph D. Rigney , Ching-Pang Lee , Ramgopal Darolia
IPC分类号： B05C13/00 , B05D1/36
CPC分类号： 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
摘要： 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.
摘要翻译：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。

64. 发明申请

US20060140768A1 Scalloped surface turbine stage 有权
公开(公告)号：US20060140768A1
公开(公告)日：2006-06-29
申请号：US11022121
申请日：2004-12-24
申请人： Anna Tam , Ching-Pang Lee , Kevin Kirtley , Ronald Bunker , Scott Lamson , Scott Carson
发明人： Anna Tam , Ching-Pang Lee , Kevin Kirtley , Ronald Bunker , Scott Lamson , Scott Carson
IPC分类号： F01D11/00
CPC分类号： F01D5/145 , F01D5/143 , F05D2240/80 , F05D2250/70 , F05D2250/711 , F05D2250/712 , Y02T50/673
摘要： A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a bulge adjoining the pressure side adjacent the leading edge, and a bowl adjoining the suction side aft of the leading edge.

65. 发明申请

US20060053800A1 HIGH THRUST GAS TURBINE ENGINE WITH IMPROVED CORE SYSTEM 有权
标题翻译：具有改进核心系统的高速涡轮发动机
公开(公告)号：US20060053800A1
公开(公告)日：2006-03-16
申请号：US10941546
申请日：2004-09-15
申请人： Robert Orlando , Kattalaicheri Venkataramani , Ching-Pang Lee , Thomas Moniz , Kurt Murrow
发明人： Robert Orlando , Kattalaicheri Venkataramani , Ching-Pang Lee , Thomas Moniz , Kurt Murrow
IPC分类号： F02C7/12
CPC分类号： F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
摘要： 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.
摘要翻译：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。

66. 发明申请

US20060051209A1 Fluted tip turbine blade 有权
标题翻译：槽形涡轮叶片
公开(公告)号：US20060051209A1
公开(公告)日：2006-03-09
申请号：US10937642
申请日：2004-09-09
申请人： Ching-Pang Lee , James Bailey , Nicholas Palmer , Wenfeng Lu
发明人： Ching-Pang Lee , James Bailey , Nicholas Palmer , Wenfeng Lu
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/20 , F01D11/08 , Y02T50/676
摘要： 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.
摘要翻译：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。

67. 发明申请

US20060029723A1 METHOD FOR REPAIRING COATED COMPONENTS USING NIAL BOND COATS 有权
标题翻译：使用NIAL BOND COATS修复涂层组件的方法
公开(公告)号：US20060029723A1
公开(公告)日：2006-02-09
申请号：US10714430
申请日：2003-11-13
申请人： Joseph Rigney , Ching-Pang Lee , Ramgopal Darolia
发明人： Joseph Rigney , Ching-Pang Lee , Ramgopal Darolia
IPC分类号： C23C16/52 , B05D3/00
CPC分类号： 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
摘要： 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.
摘要翻译：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。

68. 发明授权

US06990797B2 Methods and apparatus for operating gas turbine engines 有权
标题翻译：运行燃气轮机的方法和装置
公开(公告)号：US06990797B2
公开(公告)日：2006-01-31
申请号：US10656518
申请日：2003-09-05
申请人： Kattalaicheri Srinivasan Venkataramani , Lawrence Butler , Ching-Pang Lee
发明人： Kattalaicheri Srinivasan Venkataramani , Lawrence Butler , Ching-Pang Lee
IPC分类号： F02C7/0472 , F02K3/04
CPC分类号： F02C7/047 , F05D2260/208 , Y02T50/672 , Y02T50/675
摘要： 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.
摘要翻译：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。

69. 发明申请

US20050286998A1 Chevron film cooled wall 有权
标题翻译：雪佛龙薄膜冷却墙
公开(公告)号：US20050286998A1
公开(公告)日：2005-12-29
申请号：US10874900
申请日：2004-06-23
申请人： Ching-Pang Lee , Steven Brassfield , Ronald Bunker
发明人： Ching-Pang Lee , Steven Brassfield , Ronald Bunker
IPC分类号： B23K26/38 , F01D5/18 , F01D1/00
CPC分类号： B23K26/384
摘要： 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.
摘要翻译：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。

70. 发明申请

US20050271514A1 COATING AND COATING PROCESS INCORPORATING RAISED SURFACE FEATURES FOR AN AIR-COOLED SURFACE 有权
标题翻译：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
申请人： Ching-Pang Lee , Robert Schafrik , Ramgopal Darolia , Joseph Rigney
发明人： Ching-Pang Lee , Robert Schafrik , Ramgopal Darolia , Joseph Rigney
IPC分类号： 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分类号： 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
摘要： 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.
摘要翻译：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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