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    TRAILING EDGE DUCT FOR COMBUSTORS WITH COOLING FEATURES
    1.
    发明申请
    TRAILING EDGE DUCT FOR COMBUSTORS WITH COOLING FEATURES 审中-公开
    具有冷却功能的燃烧器的拖车边缘

    公开(公告)号：WO2017023327A1

    公开(公告)日：2017-02-09

    申请号：PCT/US2015/043959

    申请日：2015-08-06

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： FOX, Timothy A. ,  KOLSRUD, Brede ,  HARDES, Jacob William

    IPC: F01D9/02 ,  F01D25/08 ,  F01D25/12

    CPC classification number: F01D9/023 ,  F01D25/08 ,  F01D25/12 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

    Abstract: A combustor has a trailing edge duct (110) that has cooling features located at various locations. The cooling features comprise pockets (125) that have pocket channels (127) which extend from the pockets (125) to seam locations on the main duct portion (112). Additional cooling features comprise slots (132) located proximate to the pockets (125) and the trim line (131) at a distal end of the main duct portion (112). In other embodiments, cooling channels (136a, 136b, 136c) are formed on the mating surfaces (135) of the extension flange (115). Further in other embodiments, cooling features may be found in the trailing edge (120) of the trailing edge duct (110).

    Abstract translation: 燃烧器具有后缘管道（110），其具有位于各个位置处的冷却特征。 冷却特征包括具有从口袋（125）延伸到主管道部分（112）上的接缝位置的口袋通道（127）的口袋（125）。 额外的冷却特征包括位于主管道部分（112）远端处的靠近穴（125）和修剪线（131）的槽（132）。 在其他实施例中，冷却通道（136a，136b，136c）形成在延伸凸缘（115）的配合表面（135）上。 此外，在其他实施例中，可以在后缘管道（110）的后缘（120）中发现冷却特征。

    A HEAT TRANSFER DESIGN FOR PROGRESSIVE HEAT TRANSFER CAPABILITY COOLING CHANNELS
    3.
    发明申请
    A HEAT TRANSFER DESIGN FOR PROGRESSIVE HEAT TRANSFER CAPABILITY COOLING CHANNELS 审中-公开

    公开(公告)号：WO2020046379A1

    公开(公告)日：2020-03-05

    申请号：PCT/US2018/049154

    申请日：2018-08-31

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： HARDES, Jacob William ,  FOX, Timothy A.

    IPC: F01D5/18 ,  F01D9/02 ,  F23R3/00

    Abstract: A cooling channel arrangement for a region of a gas turbine engine is provided. The arrangement includes a cooling channel 26 having cooling sections 34, 36, 38 adapted for use in a component 24 with various component regions 28, 30, 32, with some sections having cooling flux mitigation adaptations to overcome the effects of increased temperature in the component regions to maintain efficient cooling effectiveness throughout the cooling channel sections. Adaptations may include regions of cross sectional area that increases heat transfer effectiveness, as well as regions characterized by an increase in lateral flow compared to longitudinal flow.

    COMPONENT HAVING IMPINGEMENT COOLED POCKETS FORMED BY RAISED RIBS AND A COVER SHEET DIFFUSION BONDED TO THE RAISED RIBS
    4.
    发明申请
    COMPONENT HAVING IMPINGEMENT COOLED POCKETS FORMED BY RAISED RIBS AND A COVER SHEET DIFFUSION BONDED TO THE RAISED RIBS 审中-公开
    具有冲击力的组件由升级的RIBS形成的冷冻口袋和覆盖片上的粘合剂

    公开(公告)号：WO2017023328A1

    公开(公告)日：2017-02-09

    申请号：PCT/US2015/043966

    申请日：2015-08-06

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： FOX, Timothy A. ,  KOLSRUD, Brede ,  HARDES, Jacob William

    IPC: F01D9/02

    CPC classification number: F01D9/023 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2240/35 ,  F05D2250/132 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/22141

    Abstract: A gas turbine engine component (10), having: a base layer (60) including an array (110) of pockets (52) separated by raised ribs (36), and a film cooling hole (70) through the base layer in each pocket; and a cover sheet (62) diffusion bonded to the raised ribs and including an impingement hole (72) for each pocket of the array of pockets. The raised ribs include a thickness (104) that is less than half of a smallest dimension (96) of the pocket. The component is configured to receive combustion gases from a combustor and accelerate and deliver the combustion gases onto a first row of turbine blades without a turning vane.

    Abstract translation: 一种燃气涡轮发动机部件（10），其具有：基部层（60），其包括通过凸肋（36）分隔开的凹部（52）的阵列（110），以及通过每个所述基部层的薄膜冷却孔（70） 口袋; 以及覆盖片（62），其扩散接合到所述凸起的肋并且包括用于所述凹穴阵列的每个凹穴的冲击孔（72）。 隆起的肋包括小于口袋的最小尺寸（96）的一半的厚度（104）。 该部件构造成从燃烧器接收燃烧气体，并将燃烧气体加速并输送到第一排涡轮机叶片上，而无需转动叶片。

    GAS TURBINE TRANSITION DUCT WITH LATE LEAN INJECTION HAVING REDUCED COMBUSTION RESIDENCE TIME
    5.
    发明申请
    GAS TURBINE TRANSITION DUCT WITH LATE LEAN INJECTION HAVING REDUCED COMBUSTION RESIDENCE TIME 审中-公开
    具有降低燃烧停留时间的轻度注射的气体涡轮转换管

    公开(公告)号：WO2017018982A1

    公开(公告)日：2017-02-02

    申请号：PCT/US2015/041948

    申请日：2015-07-24

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： LASTER, Walter Ray ,  PORTILLO BILBAO, Juan Enrique ,  FOX, Timothy A. ,  POWERS, Grant L.

    IPC: F23R3/42 ,  F23R3/06 ,  F23R3/28 ,  F23R3/34 ,  F23R3/46 ,  F01D9/02

    CPC classification number: F01D9/023 ,  F23R3/06 ,  F23R3/286 ,  F23R3/346 ,  F23R3/425 ,  F23R3/46

    Abstract: An improved gas turbine combustion system having a reduced combustion residence time in a combustion turbine engine is provided. The combustion system includes a flow-accelerating structure (16, 51), such as a transition duct, having an inlet (26) and an outlet (28). The inlet (26) of the flow-accelerating structure () is fluidly coupled to receive a flow of combustion gases from a combustor outlet. At least one fuel injector (32, 64, 66) is disposed between the inlet (26) and the outlet (28) of the flow-accelerating structure (16, 51). The flow-accelerating structure (16, 51) causes an increasing speed to the flow of combustion gases, and, as a result, the flow of combustion gases in the flow-accelerating structure (16, 51) experiences a decreased static temperature and a reduced combustion residence time, each of which is effective to reduce NOx emissions at the high firing temperatures of the turbine engine.

    Abstract translation: 提供了一种在燃气轮机中具有减少的燃烧停留时间的改进的燃气轮机燃烧系统。 燃烧系统包括具有入口（26）和出口（28）的流动加速结构（16,51），例如过渡管道。 流动加速结构（）的入口（26）流体耦合以接收来自燃烧器出口的燃烧气体流。 至少一个燃料喷射器（32,64,66）设置在流动加速结构（16,51）的入口（26）和出口（28）之间。 流动加速结构（16,51）对燃烧气体的流动造成增加的速度，结果，流动加速结构（16,51）中的燃烧气体的流动经历降低的静态温度和 减少的燃烧停留时间，其中每个都有效地减少在涡轮发动机的高燃烧温度下的NOx排放。

    COOLING FEATURES FOR A GAS TURBINE ENGINE
    6.
    发明申请
    COOLING FEATURES FOR A GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机的冷却特性

    公开(公告)号：WO2018021993A1

    公开(公告)日：2018-02-01

    申请号：PCT/US2016/043809

    申请日：2016-07-25

    Applicant: SIEMENS AKTIENGESELLSCHAFT

    Inventor： FOX, Timothy A. ,  HARDES, Jacob William

    IPC: F01D9/02 ,  F01D25/12

    Abstract: A gas turbine engine has a converging duct (10) that has combustion products flow at low mach speeds through a first portion (14) and a high mach speeds through a second portion (15). The converging duct (10) has two types of cooling schemes formed. One type of cooling scheme is beneficial for the low mach speed combustion product flow and one type of cooling scheme is beneficial for the high mach speed combustion product flow. The two cooling schemes are blended together in order increase the efficiency of the cooling of the converging duct (10).

    Abstract translation: 燃气涡轮发动机具有会聚导管（10），其具有通过第一部分（14）以低马赫速度流动并且通过第二部分（15）以高马赫速度流动的燃烧产物。 会聚管道（10）具有两种类型的冷却方案。 一种类型的冷却方案对于低马赫数速度的燃烧产物流是有利的，并且一种类型的冷却方案对于高马赫数速度的燃烧产物流是有利的。 两种冷却方案混合在一起，以提高会聚管道（10）的冷却效率。

    NOZZLE WITH MULTI-TUBE FUEL SUPPLY PASSAGEWAY FOR GAS TURBINE ENGINES
    7.
    发明申请
    NOZZLE WITH MULTI-TUBE FUEL SUPPLY PASSAGEWAY FOR GAS TURBINE ENGINES 审中-公开
    燃气涡轮发动机多管燃油喷嘴喷嘴

    公开(公告)号：WO2014123955A1

    公开(公告)日：2014-08-14

    申请号：PCT/US2014/014793

    申请日：2014-02-05

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： WILLIAMS, Steven ,  FOX, Timothy A. ,  SCHILP, Reinhard

    IPC: F23D14/22 ,  F23D14/24 ,  F23R3/34 ,  F23R3/36 ,  F23R3/38

    CPC classification number: F23R3/343 ,  F02C7/266 ,  F23D3/22 ,  F23D11/38 ,  F23D11/42 ,  F23D14/22 ,  F23D14/24 ,  F23D2207/00 ,  F23R3/36 ,  F23R3/38

    Abstract: A pilot fuel nozzle (10) for a gas turbine combustor includes an igniter (20) forming a central body (19) extending along a longitudinal center of the nozzle (10). A nozzle tip (18) includes a plurality of circumferentially spaced fuel passages (32) and a plurality of circumferentially spaced air passages (54) extending to an outer side of the nozzle tip (18). The central body (19) extends through a center of the nozzle tip (18) for producing a spark to ignite a fuel/ air mixture adjacent to the nozzle tip (18). A plurality of eventually spiral fuel tubes (32) extend along the central body (19), each of the fuel tubes (32) having an outlet end (38) engaged on the nozzle tip (18) for delivery of fuel from the nozzle tip (18) into a combustion chamber. An outer sleeve (16) surrounds the fuel tubes (32) and defines an annular space (52) in fluid communication with the air passages (54) of the nozzle tip (18) between the outer sleeve (16) and the central body (19). The outer sleeve (16) may further include an annular diffusion passage (72), and an annular premix passage (74) for additional or alternative fuel supply.

    Abstract translation: 用于燃气轮机燃烧器的先导燃料喷嘴（10）包括形成沿着喷嘴（10）的纵向中心延伸的中心体（19）的点火器（20）。 喷嘴尖端（18）包括多个周向隔开的燃料通道（32）和延伸到喷嘴尖端（18）的外侧的多个周向间隔开的空气通道（54）。 中心体（19）延伸穿过喷嘴尖端（18）的中心，用于产生火花以点燃与喷嘴尖端（18）相邻的燃料/空气混合物。 多个最终螺旋形的燃料管（32）沿着中心体（19）延伸，每个燃料管（32）具有接合在喷嘴尖端（18）上的出口端（38），用于从喷嘴尖端 （18）进入燃烧室。 外套筒（16）围绕燃料管（32）并且限定与外筒（16）和中心体（16）之间的喷嘴头（18）的空气通道（54）流体连通的环形空间（52） 19）。 外套筒（16）还可以包括环形扩散通道（72）和用于附加或替代燃料供应的环形预混通道（74）。

    COMBUSTION SYSTEM WITH INJECTOR ASSEMBLIES ARRANGED TO RECAPTURE COOLING AIR IN A COMBUSTOR WALL TO FORM A SHIELDING FLOW OF AIR IN A COMBUSTION STAGE
    8.
    发明申请
    COMBUSTION SYSTEM WITH INJECTOR ASSEMBLIES ARRANGED TO RECAPTURE COOLING AIR IN A COMBUSTOR WALL TO FORM A SHIELDING FLOW OF AIR IN A COMBUSTION STAGE 审中-公开
    燃烧系统带有喷油器组件，用于重新安装燃烧室壁内的冷却空气以形成燃烧空气的屏蔽流

    公开(公告)号：WO2018026381A1

    公开(公告)日：2018-02-08

    申请号：PCT/US2016/048837

    申请日：2016-08-26

    Applicant: SIEMENS AKTIENGESELLSCHAFT

    Inventor： NORTH, Andrew J. ,  PORTILLO BILBAO, Juan Enrique ,  LASTER, Walter Ray ,  FOX, Timothy A.

    IPC: F23R3/28 ,  F23R3/34 ,  F23R3/00 ,  F23R3/60 ,  F23R3/12

    Abstract: A combustion system in a combustion turbine engine is provided. The system may include a combustor wall (40) fluidly coupled to receive a cross-flow of combustion products (21). The combustor wall (40) may include a plurality of cooling air conduits (46). An injector assembly (12) may be in fluid communication with the cooling fluid conduits (46) to receive cooling fluid that passes through the cooling fluid conduits. Injector assembly (12) includes means for injecting (24, 25, 26) a flow of the cooling fluid (22) into the combustion stage. The flow of the cooling fluid may be arranged to condition interaction of a flow of reactants (19) injected to admix with the cross-flow of combustion products.

    Abstract translation: 提供了一种燃气轮机发动机中的燃烧系统。 该系统可以包括流体连接以接收燃烧产物（21）的交叉流动的燃烧器壁（40）。 燃烧器壁（40）可以包括多个冷却空气导管（46）。 喷射器组件（12）可以与冷却流体导管（46）流体连通以接收穿过冷却流体导管的冷却流体。 喷射器组件（12）包括用于将冷却流体（22）的流注入（24,25,26）到燃烧级中的装置。 冷却流体的流动可布置成调节注入的反应物流（19）与燃烧产物的交叉流混合的相互作用。

    SERRATED TRAILING EDGE DUCTS FOR GAS TURBINE COMBUSTORS
    9.
    发明申请
    SERRATED TRAILING EDGE DUCTS FOR GAS TURBINE COMBUSTORS 审中-公开
    用于汽轮机燃烧器的SERRATED TRAILING EDGE管道

    公开(公告)号：WO2017082876A1

    公开(公告)日：2017-05-18

    申请号：PCT/US2015/059937

    申请日：2015-11-10

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： KUMAR, Manish ,  BEECK, Alexander Ralph ,  FOX, Timothy A. ,  HARDES, Jacob William

    IPC: F01D25/30 ,  F01D9/02 ,  F23R3/42

    CPC classification number: F01D25/30 ,  F01D9/023 ,  F23R3/42 ,  F23R3/46

    Abstract: A gas engine turbine has a trailing edge duct (110) that is used for the transition duct. The trailing edge duct (110) has an extension flange (115) located at its outlet (117). The extension flange (115) has a contoured receiving section (134a, 134b, 134c) and a contoured insertion section (135a, 135b, 135c) that is connected to another trailing edge duct in order to form contoured connections (136a, 136b, 136c). The contoured receiving sections (134a, 134b, 134c) may be parabolic shaped, serrated or a combination of both parabolic shaped and serrated.

    Abstract translation: 燃气发动机涡轮机具有用于过渡管道的后缘管道（110）。 后缘管道（110）具有位于其出口（117）处的延伸凸缘（115）。 延伸凸缘（115）具有成形的接收部分（134a，134b，134c）和成形的插入部分（135a，135b，135c），所述成形的插入部分连接到另一个后缘管道以形成波状连接（136a，136b，136c ）。 波状接收部分（134a，134b，134c）可以是抛物线形，锯齿形或抛物线形和锯齿形的组合。

    TRANSITION DUCT EXIT FRAME WITH INSERT
    10.
    发明申请
    TRANSITION DUCT EXIT FRAME WITH INSERT 审中-公开

    公开(公告)号：WO2016080957A1

    公开(公告)日：2016-05-26

    申请号：PCT/US2014/066036

    申请日：2014-11-18

    Applicant: SIEMENS AKTIENGESELLSCHAFT

    Inventor： HETTINGER, Benjamin G. ,  BERTONCELLO, James ,  SCHIAVO, Anthony L. ,  FOX, Timothy A. ,  SCHILP, Reinhard

    IPC: F01D9/02 ,  F23R3/60

    CPC classification number: F01D9/023 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/642 ,  F05D2260/30 ,  F05D2300/50212 ,  F23R3/60

    Abstract: A transition duct exit frame (10) for supporting a transition duct (12) extending downstream from a combustor (14) to a turbine assembly (16) in a gas turbine engine (18) and including one or more transition duct exit frame inserts (20) configured to reduce thermal distortion created during operation of the gas turbine engine (18) is disclosed. The transition duct exit frame (10) is formed from one or more transition duct exit frame bodies (22). The transition duct exit frame body (22) is formed from a first material having a first coefficient of thermal expansion. The transition duct exit frame insert (20) forms at least a portion of the transition duct exit frame body. The transition duct exit frame insert (20) is formed from a second material (26) having a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion of the first material (24) to reduce distortion within the transition duct exit frame body (22) during operation of the gas turbine engine (18).

    Abstract translation: 一种用于支撑从燃烧器（14）的下游延伸到燃气涡轮发动机（18）中的涡轮机组件（16）的过渡管道（12）的过渡管道出口框架（10），并且包括一个或多个过渡管道出口框架插入件 公开了一种用于减少在燃气涡轮发动机（18）的运行期间产生的热变形的结构（20）。 过渡管道出口框架（10）由一个或多个过渡管道出口框架体（22）形成。 过渡管出口框架体22由具有第一热膨胀系数的第一材料形成。 过渡管道出口框架插入件（20）形成过渡管道出口框架体的至少一部分。 过渡管道出口框架插入件（20）由具有与第一材料（24）的第一热膨胀系数不同的第二热膨胀系数的第二材料（26）形成，以减少过渡管道出口 在所述燃气涡轮发动机（18）的运行期间，所述框体（22）。

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