公开(公告)号：US20100239851A1

公开(公告)日：2010-09-23

申请号：US11529453

申请日：2006-09-28

申请人： Gary Stevens ,  James D.B. Smith ,  John W. Wood

发明人： Gary Stevens ,  James D.B. Smith ,  John W. Wood

IPC分类号： B32B5/16 ,  B32B29/06 ,  C08L63/00

CPC分类号： H05K1/0373 ,  H05K2201/0209 ,  H05K2201/0224 ,  H05K2201/0248 ,  Y10T428/25 ,  Y10T428/251 ,  Y10T428/254 ,  Y10T428/256 ,  Y10T428/257 ,  Y10T428/258 ,  Y10T428/259 ,  Y10T428/31511 ,  Y10T428/31993

摘要： A high thermal conductivity resin that is made up of a host resin matrix (42) and high thermal conductivity fillers (30) that are mixed within the host resin to form a resin mixture. The fillers comprise at least 3-5% by weight of the resin mixture, and the fillers are from an average of 1-100 nm in at least one dimension, and where the particles are smaller than an average of 1000 nm in the particles' longest dimension. The host resin matrix forms an ordered resin shell (40) around the high thermal conductivity fillers (30), whereby resin molecules are aligned perpendicular to the surface of the high thermal conductivity fillers. An overlap of the ordered resin shells (44) is formed between the high thermal conductivity fillers such that continuous pathways for ordered resin shells are created through the resin mixture.

摘要翻译： 由主体树脂基体（42）和高导热性填料（30）构成的高导热性树脂，其混合在主体树脂内以形成树脂混合物。 填料包含至少3-5重量％的树脂混合物，并且填料在至少一个维度上平均为1-100nm，并且其中颗粒小于平均粒径为1000nm的颗粒' 最长尺寸。 主体树脂基体在高导热性填料（30）周围形成有序的树脂壳（40），由此树脂分子垂直于高热导率填料的表面排列。 在高导热性填料之间形成有序树脂壳（44）的重叠，使得通过树脂混合物产生有序树脂壳的连续路径。

公开(公告)号：US20100226757A1

公开(公告)日：2010-09-09

申请号：US11521193

申请日：2006-09-14

申请人： David J. Mitchell ,  Anand A. Kulkarni ,  Ramesh Subramanian ,  Edward R. Roesch

发明人： David J. Mitchell ,  Anand A. Kulkarni ,  Ramesh Subramanian ,  Edward R. Roesch

IPC分类号： F02C7/00

CPC分类号： F01D21/003 ,  B33Y80/00 ,  F01D17/02 ,  F01D21/14 ,  F05D2260/80

摘要： An instrumented component (18, 19) for use in various operating environments such as within a combustion turbine engine (10). The component (18, 19) may have a substrate, a sensor (50, 94, 134) connected with the substrate for sensing a condition of the component (18, 19) during operation of the combustion turbine (10) and a connector (52, 92, 140) attached to the substrate and in communication with the sensor (50, 94, 134) for routing a data signal from the sensor (50, 94, 134) to a termination location (53). The component (18, 19) may include a wireless telemetry device (54, 76, 96) in communication with the connector (52, 92, 140) for wirelessly transmitting the data signal. Recesses (114, 116) may be formed with a root portion (112, 132) of components (18, 19) within which wireless telemetry device (54, 76, 96) may be affixed.

摘要翻译： 一种在诸如燃气涡轮发动机（10）内的各种操作环境中使用的仪表部件（18,19）。 组件（18,19）可以具有衬底，与衬底连接的传感器（50,94,134），用于在燃气轮机（10）的操作期间感测组件（18,19）的状态和连接器 连接到所述基板并与所述传感器（50,94,134）通信，用于将数据信号从所述传感器（50,94,134）路由至终止位置（53）。 组件（18,19）可以包括与连接器（52,92,140）通信的无线遥测装置（54,76,96），用于无线地发送数据信号。 凹部（114,116）可以形成有可以固定无线遥测装置（54,76,96）的部件（18,19）的根部部分（112,132）。

公开(公告)号：US20100221121A1

公开(公告)日：2010-09-02

申请号：US11506080

申请日：2006-08-17

申请人： George Liang

发明人： George Liang

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2260/22141

摘要： A cooling system for a turbine airfoil of a turbine engine having a suction side near wall cooling chamber extending from the leading edge to the trailing edge. The suction side near wall cooling chamber may include a plurality of pin fins for increasing the cooling effectiveness of the suction side near wall cooling chamber. The pin fins may be formed in two or more regions having varying sizes and quantities per unit area to accommodate different cooling requirements across the airfoil. In one embodiment, cooling fluids may flow in a counterflow manner through the suction side near wall cooling chamber relative to a pressure side near wall cooling chamber. In another embodiment, the cooling fluids may flow from the leading edge through the suction side near wall cooling chamber and be exhausted through slots in the trailing edge.

摘要翻译： 一种用于涡轮发动机的涡轮叶片的冷却系统，其具有从前缘延伸到后缘的吸力侧近壁冷却室。 靠近壁冷却室的吸入侧可以包括用于增加靠近壁冷却室的吸入侧的冷却效果的多个销翅片。 销翅片可以形成在两个或更多个区域中，每个单位面积具有不同的尺寸和数量，以适应​​横跨翼型件的不同冷却要求。 在一个实施例中，冷却流体可以逆流方式通过靠近壁冷却室的吸入侧相对于靠近壁冷却室的压力侧流动。 在另一个实施例中，冷却流体可以从前缘流过靠近壁冷却室的吸入侧，并通过后缘中的槽排出。

公开(公告)号：US20100071373A1

公开(公告)日：2010-03-25

申请号：US12233713

申请日：2008-09-19

申请人： Scott M. Martin ,  Robert J. Bland ,  Anil Gulati

发明人： Scott M. Martin ,  Robert J. Bland ,  Anil Gulati

IPC分类号： F23R3/28 ,  F23C7/00 ,  F23D11/00

CPC分类号： F23R3/14 ,  F23C2900/07001 ,  F23D2900/00008 ,  F23D2900/00015 ,  F23D2900/14701 ,  F23R3/286 ,  F23R3/343 ,  F23R2900/03343

摘要： A pilot burner (150, 350) for a gas turbine engine delivers an inner non-swirling fuel-oxidant mixture surrounded by an outer swirling fuel-oxidant mixture, thereby providing enhanced mixing with no recirculation zone. At least one fluid-restricting inlet port (166, 366) provides an oxidant to an inner mixing passage (160, 360). The inner mixing passage (160, 360) includes a plurality of fuel outlets (168). An outer annular mixing passage (180) receives oxidant from an upstream port (181) surrounding the inner mixing passage and includes at least one swirler element (186, 386) and fuel outlets (188).

摘要翻译： 用于燃气涡轮发动机的引燃燃烧器（150,350）输送由外部旋转燃料 - 氧化剂混合物包围的内部非旋转燃料 - 氧化剂混合物，从而提供与不再循环区域的增强混合。 至少一个流体限制入口（166,366）向内部混合通道（160,360）提供氧化剂。 内部混合通道（160,360）包括多个燃料出口（168）。 外部环形混合通道（180）从围绕内部混合通道的上游端口（181）接收氧化剂，并且包括至少一个旋流器元件（186,386）和燃料出口（188）。

公开(公告)号：US20100031624A1

公开(公告)日：2010-02-11

申请号：US12175665

申请日：2008-07-18

申请人： Darren E. Austin ,  Stephen J. Young

发明人： Darren E. Austin ,  Stephen J. Young

IPC分类号： F02C7/08

CPC分类号： F02C7/224 ,  F05D2260/80 ,  F05D2270/08 ,  Y02E20/16

摘要： A method and system for heating fuel for a gas turbine engine by using excess heat energy in the engine exhaust gas to heat the fuel and returning the cooled exhaust gas back to the engine exhaust gas stream upstream of an emissions sensor is disclosed. The method and system comprises providing a heat exchanger having an exhaust gas passage and a fuel passage, extracting high temperature exhaust gas from the engine exhaust gas stream and passing the high temperature exhaust gas through the exhaust gas passage. Fuel is passed through the fuel passage where excess heat energy in the high temperature exhaust gas is used to heat the fuel. The temperature of the heated fuel is controlled by controlling the flow of the high temperature exhaust gas through the exhaust gas passage.

摘要翻译： 公开了一种通过在发动机排气中使用过量热能来加热燃料并将冷却的废气返回到排放传感器上游的发动机废气流来加热燃气涡轮发动机的燃料的方法和系统。 该方法和系统包括提供具有排气通道和燃料通道的热交换器，从发动机废气流中提取高温废气并使高温废气通过废气通道。 燃料通过燃料通道，其中使用高温废气中的多余的热能来加热燃料。 通过控制通过排气通道的高温废气的流动来控制加热燃料的温度。

公开(公告)号：US20100011776A1

公开(公告)日：2010-01-21

申请号：US12175653

申请日：2008-07-18

申请人： Ricardo F. Moraes

发明人： Ricardo F. Moraes

IPC分类号： F23R3/44 ,  B23P15/00

CPC分类号： B23P11/025 ,  F23M5/00 ,  F23M2900/05004 ,  F23R3/002 ,  F23R2900/00018

摘要： A combustor basket (20) is provided comprising a generally tubular wall (22) defining a cavity (24) and a liner (26) of a ceramic matrix composite material disposed within the cavity (24), wherein an interference fit exists between an outer surface (34) of the liner (26) located in the cavity (24) and an inner surface (28) of the generally tubular wall (22). Advantageously, the novel combustor basket (20) greatly reduces the amount of air or other medium needed to cool the combustor basket body and increases the maximum allowable flame temperature that the combustor basket (20) can withstand. A method of manufacturing the combustor basket (20) is also provided.

摘要翻译： 提供了一种燃烧器筐（20），其包括限定空腔（24）的大致管状的壁（22）和设置在空腔（24）内的陶瓷基质复合材料的衬垫（26），其中在外部 位于空腔（24）内的衬套（26）的表面（34）和大致管状壁（22）的内表面（28）。 有利地，新型燃烧器筐（20）大大减少了冷却燃烧筐体所需的空气或其它介质的量，并增加了燃烧器筐（20）可承受的最大允许火焰温度。 还提供了一种制造燃烧器筐（20）的方法。

公开(公告)号：US20090324385A1

公开(公告)日：2009-12-31

申请号：US11707192

申请日：2007-02-15

申请人： George Liang

发明人： George Liang

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/221

摘要： An airfoil is provided for a gas turbine comprising an outer structure comprising a first wall, an inner structure comprising a second wall spaced relative to the first wall such that a cooling gap is defined between at least portions of the first and second walls, and seal structure provided within the cooling gap between the first and second walls for separating the cooling gap into first and second cooling fluid impingement gaps. An inner surface of the second wall may define an inner cavity. The inner structure may further comprise a separating member for separating the inner cavity of the inner structure into a cooling fluid supply cavity and a cooling fluid collector cavity. The second wall may comprise at least one first impingement passage, at least one second impingement passage, and at least one bleed passage.

摘要翻译： 提供了一种用于燃气轮机的翼型件，其包括外部结构，该外部结构包括第一壁，内部结构，其包括相对于第一壁间隔开的第二壁，使得在第一和第二壁的至少一部分之间限定冷却间隙，并且密封 设置在第一和第二壁之间的冷却间隙内，用于将冷却间隙分离成第一和第二冷却流体冲击间隙。 第二壁的内表面可以限定内腔。 内部结构还可以包括用于将内部结构的内腔分离成冷却流体供应腔和冷却流体收集器腔的分离构件。 第二壁可以包括至少一个第一冲击通道，至少一个第二冲击通道和至少一个排放通道。

公开(公告)号：US20090320966A1

公开(公告)日：2009-12-31

申请号：US11497113

申请日：2006-08-01

申请人： James A. Morin

发明人： James A. Morin

IPC分类号： C22F1/10 ,  B23P6/00 ,  C21D9/00

CPC分类号： B23K31/02 ,  B23K35/304 ,  B23K2101/001 ,  B23P6/002 ,  C21D1/09 ,  C21D9/00 ,  C22F1/10 ,  Y10T29/49318 ,  Y10T29/49723 ,  Y10T29/49732 ,  Y10T29/49742

摘要： A method of weld repairing a superalloy material at ambient temperatures without causing cracking of the base material. A superalloy material such as CM-247 LC, as is commonly used in gas turbine blade applications, is subjected to an overage pre-weld heat treatment in order to grow the volume percentage of gamma prime precipitate in the material to a level sufficient to permit ambient temperature welding without cracking. CM-247 LC material is heated in a vacuum furnace at a rate of about 0.5° C. per minute to an intermediate temperature of about 885° C. The material is then gas fan quenched to a temperature of about 52° C. to grow the gamma prime precipitate percentage to about 55%. A fusion repair weld may then be performed on the material at an ambient temperature using a filler material having a chemistry matching a chemistry of the base material.

摘要翻译： 在环境温度下焊接修复超合金材料而不引起基体材料破裂的方法。 在燃气轮机叶片应用中通常使用的诸如CM-247LC的超级合金材料经受过度预焊接热处理，以将材料中的γ'沉淀物的体积百分比增加至足以允许 环境温度焊接无裂纹。 CM-247 LC材料在真空炉中以约0.5℃/分钟的速率加热至约885℃的中间温度。然后将材料淬火至约52℃的温度以生长 γ'沉淀百分比至约55％。 然后可以使用具有与基材的化学性质匹配的化学物质的填充材料在环境温度下对材料进行熔融修补焊缝。

公开(公告)号：US20090263243A1

公开(公告)日：2009-10-22

申请号：US12106375

申请日：2008-04-21

申请人： David A. Little ,  Hubertus E. Paprotna ,  Kevin M. Light

发明人： David A. Little ,  Hubertus E. Paprotna ,  Kevin M. Light

IPC分类号： F01D25/14

CPC分类号： F01D25/14

摘要： A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively.

摘要翻译： 燃气轮机包括压缩机部分，压缩机部分下游的燃烧部分和燃烧部分下游的涡轮部分。 扩散器部分在涡轮机部分的下游，并且具有外壁，内壁和在它们之间延伸的至少一个支柱构件。 外壁在其中具有至少一个第一气体通道，内壁在其中具有至少一个第二气体通道，并且至少一个支柱构件在其中具有至少一个第三气体通道。 所述至少一个第一，第二和第三气体通道输送气体通过其中以帮助边界层分别附接到外壁，内壁和至少一个支柱的相邻表面。

公开(公告)号：US20090243419A1

公开(公告)日：2009-10-01

申请号：US12055465

申请日：2008-03-26

申请人： Benjamin T. Humphries ,  Constance M. Smith ,  James F. Lau

发明人： Benjamin T. Humphries ,  Constance M. Smith ,  James F. Lau

IPC分类号： H02K3/40 ,  G01L1/10

CPC分类号： G01M7/00

摘要： A method for measuring a tangential tightness of a stator coil within an armature slot of a stator assembly in an electric generator. The stator coil is excited to produce a vibratory response therein. The vibratory response of the stator coil is detected and a frequency response function of the vibratory response is determined. A tangential tightness of the stator coil within the armature slot is estimated based on the frequency response function of the vibratory response of the stator coil.

摘要翻译： 一种用于测量发电机中的定子组件的电枢槽内的定子线圈的切向紧密度的方法。 定子线圈被激励以在其中产生振动响应。 检测定子线圈的振动响应，并确定振动响应的频率响应函数。 基于定子线圈的振动响应的频率响应函数来估计电枢槽内的定子线圈的切向紧密度。