公开(公告)号：US20080230379A1

公开(公告)日：2008-09-25

申请号：US11726418

申请日：2007-03-22

Applicant: Ching-Pang Lee ,  Bin Wei ,  Chen-Yu Jack Chou

Inventor： Ching-Pang Lee ,  Bin Wei ,  Chen-Yu Jack Chou

IPC: B23H3/00

CPC classification number: B23H3/06 ,  B23H3/00 ,  B23H3/04 ,  B23H9/10 ,  B23H9/14 ,  F01D5/18 ,  F05D2230/11

Abstract: A method for forming a hole in an object is provided. The method includes forming a starter hole in the object, providing an electrochemical machining electrode that includes insulation that extends only partially around the electrode, and inserting the electrode into the starter hole to form a hole in the object that has an inlet defined by a first cross-sectional area and an outlet defined by a second cross-sectional area.

Abstract translation: 提供了一种在物体中形成孔的方法。 该方法包括在物体中形成起动器孔，提供电化学加工电极，其包括仅部分地围绕电极延伸的绝缘体，以及将电极插入起动器孔中以在物体中形成孔，该孔具有由第一 横截面积和由第二横截面积限定的出口。

公开(公告)号：US20080229751A1

公开(公告)日：2008-09-25

申请号：US11657829

申请日：2007-01-25

Applicant: Robert Joseph Orlando ,  Kattalaicheri Srinivasan Venkataramani ,  Ching-Pang Lee

Inventor： Robert Joseph Orlando ,  Kattalaicheri Srinivasan Venkataramani ,  Ching-Pang Lee

IPC: F02C7/08

CPC classification number: F02K3/06 ,  F02C7/224 ,  F23D2214/00 ,  F23R3/28

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 booster compressor, the core system further comprising 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; 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; and, a system for cooling the combustion system, wherein fuel is utilized as a cooling fluid prior to being supplied to the combustion system. The core system may further include an intermediate compressor positioned downstream of and in flow communication with the compressor connected to a second drive shaft; and an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid.

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 ; 位于增压压缩机下游的核心系统，所述核心系统还包括燃烧系统，用于从提供给其入口的流体流产生具有增加的压力和温度的气体脉冲，以便在出口处产生工作流体; 位于所述核心系统下游并与所述核心系统流动连通的低压涡轮机，所述低压涡轮机用于为所述第一驱动轴提供动力; 以及用于冷却燃烧系统的系统，其中燃料在被供应到燃烧系统之前用作冷却流体。 核心系统可以进一步包括位于与连接到第二驱动轴的压缩机下游并与其连通的中间压缩机; 以及位于与工作流体流动连通的燃烧系统下游的中间涡轮机。

公开(公告)号：US07419352B2

公开(公告)日：2008-09-02

申请号：US11538273

申请日：2006-10-03

Applicant: Joseph M. Guentert ,  Ching-Pang Lee

Inventor： Joseph M. Guentert ,  Ching-Pang Lee

IPC: F01D9/04

CPC classification number: F01D25/246 ,  F01D11/005 ,  F05D2240/57

Abstract: A method for assembling a gas turbine engine is provided. The method includes providing a turbine nozzle including an outer band and an inner band, wherein each band includes a leading edge, a trailing edge, and a body extending therebetween. At least one of the outer band and the inner band has at least one radial tab extending outward therefrom. The method also includes coupling at least one seal between at least one of the radial tabs extending from the outer band and the inner band and a respective leading edge of the outer and inner band. The method also includes positioning at least one non-planar seal support against at least one portion of the seal.

Abstract translation: 提供一种用于组装燃气涡轮发动机的方法。 该方法包括提供包括外带和内带的涡轮喷嘴，其中每个带包括前缘，后缘和在其间延伸的本体。 外带和内带中的至少一个具有从其向外延伸的至少一个径向突片。 该方法还包括在从外带和内带延伸的至少一个径向突片和外带和内带的相应前缘之间联接至少一个密封件。 该方法还包括将至少一个非平面密封支撑件定位在密封件的至少一部分上。

公开(公告)号：US20080190582A1

公开(公告)日：2008-08-14

申请号：US11567521

申请日：2006-12-06

Applicant: Ching-Pang Lee ,  Hsin-Pang Wang

Inventor： Ching-Pang Lee ,  Hsin-Pang Wang

IPC: B22C9/00 ,  B22C9/10

CPC classification number: B22C9/04 ,  B22C9/103

Abstract: Disclosed herein is an article comprising a solidified first portion of a ceramic core; wherein the first solidified portion is manufactured by a process comprising disposing a slurry comprising ceramic particles into a metal core die; wherein an internal volume of the metal core die has a geometry equivalent to a portion of the geometry of the integral casting core; curing the slurry to form a cured first portion of the ceramic core; firing the cured first portion of the ceramic core to form a solidified first portion of the ceramic core; and a solidified second portion of the ceramic core; wherein the solidified second portion is disposed upon the solidified first portion of the ceramic core by laser consolidation.

Abstract translation: 本文公开了包含陶瓷芯的固化的第一部分的制品; 其中所述第一固化部分通过包括将包含陶瓷颗粒的浆料放置在金属芯模中的方法制造; 其中所述金属芯片的内部体积具有等同于所述整体铸造芯的几何形状的一部分的几何形状; 固化浆料以形成陶瓷芯的固化的第一部分; 焙烧固化的陶瓷芯的第一部分以形成陶瓷芯的固化的第一部分; 和陶瓷芯的固化的第二部分; 其中固化的第二部分通过激光固结设置在陶瓷芯的固化的第一部分上。

公开(公告)号：US20080148564A1

公开(公告)日：2008-06-26

申请号：US11615514

申请日：2006-12-22

Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

IPC: F01D5/02

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49236

Abstract: A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.

Abstract translation: 一种用于燃气涡轮发动机的涡轮组件。 涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。 定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。 翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。 涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。 叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。 与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。

公开(公告)号：US07387492B2

公开(公告)日：2008-06-17

申请号：US11312059

申请日：2005-12-20

Applicant: Tingfan Pang ,  Ching-Pang Lee ,  Kevin Samuel Klasing ,  Steven Robert Brassfield

Inventor： Tingfan Pang ,  Ching-Pang Lee ,  Kevin Samuel Klasing ,  Steven Robert Brassfield

IPC: F01D25/12

CPC classification number: F01D5/186 ,  F05D2240/122 ,  F05D2240/304 ,  Y02T50/676

Abstract: A method facilitates fabricating an airfoil for use with a turbine blade. The method comprises forming a substantially solid ceramic airfoil core, inserting the core into a die and casting the airfoil with a pressure side wall and a suction side wall connected together at a leading edge and a trailing edge, such that a plurality of first trailing edge slots and at least one second trailing edge slot extend from the trailing edge along the pressure side wall, wherein the second trailing edge slot has a length, measured between an inlet and an exit of the slot, that is longer than a corresponding length of each of the plurality of first trailing edge slots.

Abstract translation: 一种方法有助于制造与涡轮叶片一起使用的翼型件。 该方法包括形成基本上固体的陶瓷翼型芯，将芯插入模具中并且在前缘和后缘连接有压力侧壁和吸力侧壁的情况下铸造翼型件，使得多个第一后缘 槽和至少一个第二后缘槽沿着所述压力侧壁从所述后缘延伸，其中所述第二后缘槽具有在所述槽的入口和出口之间测量的长度，所述长度大于每个的相应长度 的多个第一后缘槽。

公开(公告)号：US20080135530A1

公开(公告)日：2008-06-12

申请号：US11609150

申请日：2006-12-11

Applicant: Ching-Pang Lee ,  Hsin-Pang Wang ,  Ronald Scott Bunker ,  Sudhir Kumar Tewari ,  Magdi Naim Azer

Inventor： Ching-Pang Lee ,  Hsin-Pang Wang ,  Ronald Scott Bunker ,  Sudhir Kumar Tewari ,  Magdi Naim Azer

IPC: B23K26/20 ,  B23P15/02

CPC classification number: F01D5/145 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  C23C24/10 ,  C23C26/02 ,  F05D2230/234 ,  F05D2230/30 ,  F05D2230/50 ,  F05D2270/17 ,  Y02P10/295 ,  Y10T29/49238 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49746

Abstract: Disclosed herein is a method comprising creating a weld pool using a laser; wherein the weld pool is created on a part of a turbine; and wherein the weld pool comprises molten metal or ceramic derived as a result of a heat interaction between the laser and the part of the turbine; adding a metal or a ceramic powder or a wire filler to the melt pool; and modifying the part of the turbine in a manner that results in a change of about 0.005 to about 50 volume percent in the part of the turbine, while improving the aerodynamic efficiency of the turbine in an amount of about 0.1 to about 5 percent over a corresponding unmodified turbine.

Abstract translation: 本文公开了一种包括使用激光产生熔池的方法; 其中所述熔池在涡轮机的一部分上产生; 并且其中所述熔池包括由于所述激光器和所述涡轮机的所述部分之间的热相互作用而导出的熔融金属或陶瓷; 在熔池中加入金属或陶瓷粉末或丝线填料; 并且以在涡轮机部分中导致约0.005至约50体积％的变化的方式修改涡轮机的一部分，同时以相对于涡轮机的大约0.1％至大约5％的量改进涡轮机的空气动力学效率 相应的未修改的涡轮机。

公开(公告)号：US20080131261A1

公开(公告)日：2008-06-05

申请号：US11565273

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

IPC: F01D5/18 ,  B21D53/78 ,  F01D1/02

CPC classification number: F01D9/04 ,  F01D11/08 ,  F05D2240/11 ,  F05D2240/81 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49346 ,  Y10T29/53443

Abstract: A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment, and channeling the cooling fluid through at least a first group of cooling openings having a larger aggregate cross-sectional area and a second group of cooling openings having a smaller aggregate cross-sectional area to facilitate preferential cooling of the turbine shroud.

Abstract translation: 提供一种组装燃气涡轮发动机的方法。 该方法包括联接燃气涡轮发动机内的至少一个涡轮喷嘴段。 至少一个涡轮喷嘴段包括在内带和外带之间延伸的至少一个翼型叶片，其包括后翼缘和径向内表面。 该方法还包括将至少一个涡轮机护罩区段联接在至少一个涡轮喷嘴段的下游，其中至少一个涡轮机护罩段包括前缘和径向内表面，将与流体连通的冷却流体源 至少一个涡轮喷嘴段，使得被引导到每个涡轮喷嘴外带后缘的冷却流体朝向至少一个涡轮机护罩段的前缘以倾斜的排出角度引导，并且通过至少一个第一组 具有较大聚集体横截面面积的冷却开口和具有较小聚集体横截面积的第二组冷却开口，以便于涡轮机护罩的优先冷却。

公开(公告)号：US20080131259A1

公开(公告)日：2008-06-05

申请号：US11565176

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

IPC: F01D25/12

CPC classification number: F01D11/24 ,  F05D2240/11 ,  Y02T50/671

Abstract: A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, and directing the cooling air in the gap through at least one cooling hole extending between the leading edge and the inner surface.

Abstract translation: 提供了一种用于冷却燃气涡轮发动机的护罩部分的方法。 该方法包括提供一种涡轮机护罩组件，其包括具有内表面和大致垂直于内表面的前缘的护罩区段，以及将涡轮喷嘴连接到涡轮机护罩区段，使得间隙限定在 涡轮喷嘴的外带和前缘。 该方法还包括将冷却空气引导到间隙中，以及通过在前缘和内表面之间延伸的至少一个冷却孔将间隙中的冷却空气引导。

公开(公告)号：US20080127491A1

公开(公告)日：2008-06-05

申请号：US11565253

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

IPC: B23P15/00 ,  F01D5/08

CPC classification number: F01D11/08 ,  F05D2240/11 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49236

Abstract: A method of assembling a gas turbine engine includes coupling a turbine shroud assembly within the gas turbine engine. The turbine shroud assembly includes a shroud segment having a leading edge defining a forward face and a radial inner surface. 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. A plurality of recuperated cooling openings are defined through the leading edge at an oblique inlet angle with respect to a centerline of the gap and between the forward face and the radial inner surface to direct cooling fluid through the leading edge to facilitate preferential cooling of the leading edge.

Abstract translation: 一种组装燃气涡轮发动机的方法包括将涡轮机罩组件联接在燃气涡轮发动机内。 涡轮机罩组件包括具有限定前表面和径向内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后表面和前表面之间限定间隙。 多个恢复的冷却开口通过前缘以相对于间隙的中心线和前表面和径向内表面之间的倾斜入口角度定义，以将冷却流体引导通过前缘，以便于优先冷却前导 边缘。