公开(公告)号：US07140835B2

公开(公告)日：2006-11-28

申请号：US10956299

申请日：2004-10-01

Applicant: Ching-Pang Lee ,  Baolan Shi ,  Wenfeng Lu ,  Joseph Michael Guentert ,  Steven Robert Brassfield

Inventor： Ching-Pang Lee ,  Baolan Shi ,  Wenfeng Lu ,  Joseph Michael Guentert ,  Steven Robert Brassfield

IPC: F01D9/02

CPC classification number: F01D5/187 ,  F05D2240/81 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.

Abstract translation: 涡轮喷嘴包括连接到相对的内部和外部带的中空叶片。 内带包括在叶片的前缘下方的前唇，在叶片的后缘下方的后唇，以及间隔开的安装凸缘。 冲击孔从安装凸缘的底部在内带的角部向后缘倾斜地向后延伸，用于冲​​击冷却。

公开(公告)号：US20060207261A1

公开(公告)日：2006-09-21

申请号：US10803293

申请日：2004-03-18

Applicant: Kattalaicheri Venkataramani ,  Lawrence Butler ,  Ching-Pang Lee

Inventor： Kattalaicheri Venkataramani ,  Lawrence Butler ,  Ching-Pang Lee

IPC: F02C5/04 ,  F02K7/02

CPC classification number: F02K7/02 ,  Y02T50/671

Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough. The pulse detonation system includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages are disposed therethrough. Each detonation passage further includes: a leading portion positioned adjacent the forward surface of the cylindrical member, with the leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to the longitudinal centerline axis within a specified plane; a trailing portion positioned adjacent the aft surface of the cylindrical member, with the trailing portion having a centerline therethrough oriented at a designated angle to the axis within the specified plane; and, a middle portion connecting the leading and trailing portions, with the middle portion having a centerline therethrough with a substantially constantly changing slope in the specified plane. A shaft is rotatably connected to the cylindrical member and a stator is configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator further includes at least one group of ports formed therein alignable with the leading portions of the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases interact therewith to create a torque which causes the cylindrical member to rotate.

Abstract translation: 一种用于燃气涡轮发动机的脉冲爆震系统，其具有延伸穿过其中的纵向中心线轴线。 脉冲爆震系统包括具有前表面，后表面和外圆周表面的可旋转圆柱形构件，其中周向间隔开的爆炸通道的至少一级设置穿过其中。 每个引爆通道还包括：与圆柱形构件的前表面相邻定位的引导部分，前导部分具有穿过中心线的中心线，该中心线以与指定平面内的纵向中心线轴线基本平行延伸的轴指定角度定位; 后部部分邻近圆柱形构件的后表面定位，后部具有穿过其中心线的中心线，该中心线以指定平面内的轴线指定角度; 以及连接前后部分的中间部分，其中间部分具有穿过其中心线的特定平面内基本上恒定变化的倾斜度。 轴可旋转地连接到圆柱形构件，并且定子被构造成与圆柱形构件的前表面和轴的一部分隔开布置。 定子还包括至少一组在圆柱形构件旋转时可与引爆通道的引导部分对准的端口。 以这种方式，在引爆通道中执行爆震循环，使得燃烧气体与其起作用以产生使圆柱形构件旋转的扭矩。

公开(公告)号：US07108479B2

公开(公告)日：2006-09-19

申请号：US10465328

申请日：2003-06-19

Applicant: Michael Beverley ,  Darek Zatorski ,  Ching-Pang Lee

Inventor： Michael Beverley ,  Darek Zatorski ,  Ching-Pang Lee

IPC: F01D5/14 ,  F03B11/00 ,  F04D29/38

CPC classification number: F01D9/06 ,  F01D5/187 ,  F01D9/041 ,  F05D2240/12 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/221 ,  Y02T50/673 ,  Y02T50/676

Abstract: A method enables a gas turbine engine to be operated. The method comprises supplying cooling fluid into a manifold ring that includes a plurality of distribution ports defined by a sidewall connected by a radially inner wall, channeling the cooling fluid circumferentially through the manifold ring and through at least one distribution port that is defined by a wall that extends arcuately across at least one turbine nozzle, and discharging cooling fluid from the distribution ports radially inwardly towards the at least one turbine nozzle positioned radially inward from the manifold ring.

Abstract translation: 一种方法使燃气涡轮发动机能够运转。 该方法包括将冷却流体供应到歧管环中，歧管环包括多个分配端口，该多个分配端口由通过径向内壁连接的侧壁限定，将冷却流体周向地引导通过歧管环，并通过至少一个由壁限定的分配端口 其横跨至少一个涡轮喷嘴弧形地延伸，并且将冷却流体从分配端口径向向内排放到从歧管环径向向内定位的至少一个涡轮喷嘴。

公开(公告)号：US07096674B2

公开(公告)日：2006-08-29

申请号：US10941546

申请日：2004-09-15

Applicant: Robert Joseph Orlando ,  Kattalaicheri Srinivasan Venkataramani ,  Ching-Pang Lee ,  Thomas Ory Moniz ,  Kurt David Murrow

Inventor： Robert Joseph Orlando ,  Kattalaicheri Srinivasan Venkataramani ,  Ching-Pang Lee ,  Thomas Ory Moniz ,  Kurt David Murrow

IPC: F02C6/08

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。

公开(公告)号：US07078073B2

公开(公告)日：2006-07-18

申请号：US10714213

申请日：2003-11-13

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

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

IPC: B05D1/36 ,  B05D3/12

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：US20060138195A1

公开(公告)日：2006-06-29

申请号：US11054635

申请日：2005-02-08

Applicant: Wayne Hasz ,  Nesim Abuaf ,  Robert Johnson ,  Ching-Pang Lee

Inventor： Wayne Hasz ,  Nesim Abuaf ,  Robert Johnson ,  Ching-Pang Lee

IPC: A47J36/02

CPC classification number: F28F13/18 ,  B23K35/30 ,  F01D5/147 ,  F01D5/186 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/23 ,  F05D2230/40 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2300/132 ,  F05D2300/172 ,  F05D2300/222 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12993

Abstract: A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.

Abstract translation: 描述了在通道孔（例如，涡轮机冷却孔）的内表面上提供紊流的方法。 首先将该紊乱施加到最终可以插入通道孔中的基底。 基板通常是由牺牲材料形成的棒或管。 在对基板施加了混浊之后，将基板插入到通孔中。 然后使用常规的加热技术将紊乱材料熔合到内表面。 然后可以通过各种技术从孔中去除牺牲衬底。 还描述了相关文章。

公开(公告)号：US20060073011A1

公开(公告)日：2006-04-06

申请号：US10956299

申请日：2004-10-01

Applicant: Ching-Pang Lee ,  Baolan Shi ,  Wenfeng Lu ,  Joseph Guentert ,  Steven Brassfield

Inventor： Ching-Pang Lee ,  Baolan Shi ,  Wenfeng Lu ,  Joseph Guentert ,  Steven Brassfield

IPC: F01D9/00

CPC classification number: F01D5/187 ,  F05D2240/81 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.

公开(公告)号：US06981841B2

公开(公告)日：2006-01-03

申请号：US10718149

申请日：2003-11-20

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

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

IPC: F03D11/00

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：US06919121B2

公开(公告)日：2005-07-19

申请号：US10153929

申请日：2002-05-23

Applicant: William R. Stowell ,  Robert A. Johnson ,  Andrew J. Skoog ,  Joseph Thomas Begovich ,  Thomas Walter Rentz ,  Jane Ann Murphy ,  Ching-Pang Lee ,  Dainel P. Ivkovich, Jr.

Inventor： William R. Stowell ,  Robert A. Johnson ,  Andrew J. Skoog ,  Joseph Thomas Begovich ,  Thomas Walter Rentz ,  Jane Ann Murphy ,  Ching-Pang Lee ,  Dainel P. Ivkovich, Jr.

IPC: F01D5/28 ,  C23C4/10 ,  C23C18/06 ,  C23C18/12 ,  C23C24/08 ,  C23C26/00 ,  C23C28/00 ,  F02C7/00 ,  B32B35/00

CPC classification number: C23C24/08 ,  Y02T50/67 ,  Y10T428/20 ,  Y10T428/24479 ,  Y10T428/24521 ,  Y10T428/25 ,  Y10T428/252

Abstract: A method of repairing a thermal barrier coating (16) on a component (10) designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method more particularly involves repairing a thermal barrier coating (16) on a component (10) that has suffered localized spallation (20) of the thermal barrier coating (16). After cleaning the surface area (22) of the component (10) exposed by the localized spallation (20), a ceramic paste (24) comprising a ceramic powder in a binder is applied to the surface area (22) of the component (10). The binder is then reacted to yield a ceramic-containing repair coating (26) that covers the surface area of the component and comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic, such that the repair coating (26) has a ceramic matrix. The repair method can be performed while the component (10) remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbine engine can resume operation during which the binder is further reacted/converted and the strength of the repair coating increases.

Abstract translation: 修复设计用于恶劣热环境的部件（10）上的热障涂层（16）的方法，所述部件（10）用于燃气涡轮发动机的涡轮机，燃烧器和增压器部件。 该方法更具体地涉及修复已经遭受热隔离涂层（16）的局部剥落（20）的部件（10）上的热障涂层（16）。 在清洁通过局部剥离（20）暴露的组分（10）的表面积（22）之后，将包含粘合剂中的陶瓷粉末的陶瓷浆料（24）施加到组分（10）的表面区域（22） ）。 然后使粘合剂反应以产生覆盖部件的表面积的含陶瓷的修补涂层（26），并且将包含在粘合剂反应时形成的材料的基质中的陶瓷粉末。 粘合剂优选是陶瓷前体材料，其可以立即转化为陶瓷或随时间而热分解形成陶瓷，使得修补涂层（26）具有陶瓷基体。 可以在组件（10）保持安装（例如，在燃气涡轮发动机中）的情况下执行修理方法。 在反应步骤之后，燃气涡轮发动机可以立即恢复操作，在此期间粘合剂进一步反应/转化，并且修复涂层的强度增加。

公开(公告)号：US06910620B2

公开(公告)日：2005-06-28

申请号：US10271098

申请日：2002-10-15

Applicant: Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson ,  Ching-Pang Lee

Inventor： Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson ,  Ching-Pang Lee

IPC: F01D5/08 ,  B23K35/30 ,  C22C19/05 ,  C22C19/07 ,  C22C38/00 ,  F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F02C7/00 ,  F28F13/18 ,  B23K35/12 ,  B05D3/02 ,  B23K31/00

CPC classification number: F28F13/18 ,  B23K35/30 ,  F01D5/147 ,  F01D5/186 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/23 ,  F05D2230/40 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2300/132 ,  F05D2300/172 ,  F05D2300/222 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12993

Abstract: A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.

Abstract translation: 描述了在通道孔（例如，涡轮机冷却孔）的内表面上提供紊流的方法。 首先将该紊乱施加到最终可以插入通道孔中的基底。 基板通常是由牺牲材料形成的棒或管。 在对基板施加了混浊之后，将基板插入到通孔中。 然后使用常规的加热技术将紊乱材料熔合到内表面。 然后可以通过各种技术从孔中去除牺牲衬底。 还描述了相关文章。