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    Atomizing air heat for attemperation
    4.
    发明公开
    Atomizing air heat for attemperation 审中-公开
    Zerstäubungvon HeissluftfürWärmeregulierung

    公开(公告)号：EP2725213A2

    公开(公告)日：2014-04-30

    申请号：EP13188625.1

    申请日：2013-10-15

    申请人： General Electric Company

    发明人： John, Joseph ,  Smith, Raub Warfield ,  Pemmi, Bhaskar ,  Muthaiah, Veerappan

    IPC分类号： F02C3/30 ,  F02C7/18 ,  F02C7/236

    CPC分类号： F02C3/30 ,  F01K23/10 ,  F02C7/14 ,  F02C7/141 ,  F02C7/185 ,  F02C7/2365 ,  F05D2260/20 ,  F05D2260/205 ,  F05D2260/2322 ,  Y02E20/16

    摘要： An attemperation system and an atomizing air system are integrated for a combined cycle turbine including a gas turbine 10 and a steam turbine 12. The atomizing air system 14 receives compressor discharge air for fuel atomization. The atomizing air system 14 includes an atomizing air cooler 18 that serves to cool the compressor discharge air. A heat recovery steam generator 121 receives exhaust from the gas turbine 10 and generates steam for input to the steam turbine 12 via an attemperation system. A feed water circuit 28, 30 draws feed water from the heat recovery steam generator 121 and communicates in a heat exchange relationship with the atomizing air cooler 18 to heat the feed water. The feed water circuit 28, 30 communicates the heated feed water to the attemperation system of the heat recovery steam generator 121.

    摘要翻译： 包括燃气轮机10和蒸汽轮机12的组合循环涡轮机组合了调温系统和雾化空气系统。雾化空气系统14接收用于燃料雾化的压缩机排出空气。 雾化空气系统14包括用于冷却压缩机排出空气的雾化空气冷却器18。 热回收蒸汽发生器121接收来自燃气轮机10的排气，并且通过调温系统产生用于输入到汽轮机12的蒸汽。 给水回路28,30从热回收蒸汽发生器121抽取供水，并与雾化空气冷却器18以热交换关系连通，以加热给水。 给水回路28,30将加热的供水与热回收蒸汽发生器121的调温系统连通。

    Gas turbine
    5.
    发明公开
    Gas turbine 有权
    燃气轮机

    公开(公告)号：EP1128039A2

    公开(公告)日：2001-08-29

    申请号：EP00118535.4

    申请日：2000-08-25

    申请人： Hitachi, Ltd.

    发明人： Yamanaka, Kazunori ,  Kondou, Satoshi ,  Noda, Masami

    IPC分类号： F02C7/236 ,  F02C7/18

    CPC分类号： F02C7/18 ,  F02C3/10 ,  F02C7/143 ,  F02C7/185 ,  F02C7/2365

    摘要： A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.

    摘要翻译： 燃气轮机具有供给用于冷却燃气轮机的高温部分的空气的冷却空气系统和向燃烧器喷射燃料而供给空气的喷射空气系统，并且形成为使得由燃气轮机压缩的高压空气的一部分 压缩机用作冷却空气系统和喷射空气系统的空气，其中热交换器和增压压缩机布置在燃气轮机压缩机的压缩空气出口的下游，并且增压压缩机由 由涡轮机轴驱动的压缩机和由涡轮机轴以外的驱动源驱动的压缩机，而来自增压压缩机的加压空气用作冷却空气系统和喷射空气系统的空气。

    Dual-orifice bypass system for duel-fuel gas turbine
    6.
    发明公开
    Dual-orifice bypass system for duel-fuel gas turbine 有权
    DoppelöffnungbypasssystemfürGasturbine mitZweibrennstoffdüse

    公开(公告)号：EP1124047A1

    公开(公告)日：2001-08-16

    申请号：EP00301014.7

    申请日：2000-02-09

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Kaplan, Howard Jay ,  Stimpson, Joel Thomas

    IPC分类号： F02C7/18 ,  F02C7/236

    CPC分类号： F02C7/2365 ,  F02C7/185

    摘要： Compressor discharge air flows through a heat exchanger (50) in heat exchange relation with cooling water and is supplied at reduced temperature in atomizing air and purge modes to combustors in a dual-fuel gas turbine. The heat exchanger has a pair of bypass passages (64, 66) in parallel with a temperature regulating valve (58) controlling flow of water through the heat exchanger (50) in response to the temperature of the compressor discharge air exiting the heat exchanger (50). Should the flow control valve (58) close in response to low temperature of the compressor discharge air, in the air atomizing mode, the bypass passages (64, 66) with orifices (68, 72) therein provide a minimum protective flow of cooling water to the heat exchanger (50). In the purge mode where only half the air flow and heat rejection is required in the heat exchanger (50) and the flow control valve (58) closes, a bypass valve (74) in one of the bypass passages (66) closes to enable reduced flow of cooling water through the heat exchanger (50).

    摘要翻译： 压缩机排放空气通过与冷却水热交换的热交换器（50）流动并且在降低的温度下以雾化空气和吹扫模式供应到双燃料燃气轮机中的燃烧器。 热交换器具有与温度调节阀（58）并联的一对旁通通道（64,66），温度调节阀（58）响应于离开热交换器的压缩机排出空气的温度来控制通过热交换器（50）的水流（ 50）。 如果流量控制阀（58）响应于压缩机排放空气的低温而关闭，则在空气雾化模式中，其中具有孔口（68,72）的旁通通道（64,66）提供冷却水的最小保护流量 到所述热交换器（50）。 在吹扫模式中，在热交换器（50）和流量控制阀（58）中只需要一半的空气流量和排热量，一个旁路通道（66）中的旁通阀（74）关闭，使得能够 减少冷却水流过热交换器（50）。

    Turbocooler air assist fuel atomization in a gas turbine engine
    7.
    发明公开
    Turbocooler air assist fuel atomization in a gas turbine engine 失效
    在燃气涡轮机的燃料雾化，通过冷却空气的装置预冷却

    公开(公告)号：EP0851105A3

    公开(公告)日：2000-04-12

    申请号：EP97310306.2

    申请日：1997-12-19

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Coffinberry, George Albert

    IPC分类号： F02C7/236 ,  F02C7/18 ,  F23R3/00

    CPC分类号： F02C7/2365

    摘要： A gas turbine engine including a turbocooler and configure so that, in one embodiment, cool air from the turbocooler is supplied to the combustor (10) for cooling the combustor (10) and then, after cooling at least a portion of the combustor (10), for mixing with fuel in the fuel injector (30), is described. In one form, the combustor (10) includes a flowpath (42) in flow communication with cool air supplied by the turbocooler. The air flows through the flowpath from an aft portion to an outlet located at the fuel injector (30) The cooling air, after having cooled walls of the combustion chamber (18), mixes with fuel in the fuel injector (30). Mixing the high pressure air form the turbocooler with the fuel in the fuel injector (30) facilitates dispersion of fuel from the fuel injector (30) into the combustion chamber (18), and also aids in increasing the fuel/air energy shear gradients. As a result, the injection velocity is believed to be significantly increased, and NOx emissions are believed to be reduced.

    Atomizing air heat for attemperation
    8.
    发明公开
    Atomizing air heat for attemperation 审中-公开
    雾化空气热量进行调理

    公开(公告)号：EP2725213A3

    公开(公告)日：2017-11-29

    申请号：EP13188625.1

    申请日：2013-10-15

    申请人： General Electric Company

    发明人： John, Joseph ,  Smith, Raub Warfield ,  Pemmi, Bhaskar ,  Muthaiah, Veerappan

    IPC分类号： F02C3/30 ,  F02C7/18 ,  F02C7/236

    CPC分类号： F02C3/30 ,  F01K23/10 ,  F02C7/14 ,  F02C7/141 ,  F02C7/185 ,  F02C7/2365 ,  F05D2260/20 ,  F05D2260/205 ,  F05D2260/2322 ,  Y02E20/16

    摘要： An attemperation system and an atomizing air system are integrated for a combined cycle turbine including a gas turbine 10 and a steam turbine 12. The atomizing air system 14 receives compressor discharge air for fuel atomization. The atomizing air system 14 includes an atomizing air cooler 18 that serves to cool the compressor discharge air. A heat recovery steam generator 121 receives exhaust from the gas turbine 10 and generates steam for input to the steam turbine 12 via an attemperation system. A feed water circuit 28, 30 draws feed water from the heat recovery steam generator 121 and communicates in a heat exchange relationship with the atomizing air cooler 18 to heat the feed water. The feed water circuit 28, 30 communicates the heated feed water to the attemperation system of the heat recovery steam generator 121.

    摘要翻译： 调温系统和雾化空气系统集成用于包括燃气涡轮机10和蒸汽涡轮机12的联合循环涡轮机。雾化空气系统14接收用于燃料雾化的压缩机排气。 雾化空气系统14包括用于冷却压缩机排出空气的雾化空气冷却器18。 热回收蒸汽发生器121接收来自燃气涡轮机10的排气并产生蒸汽以经由调温系统输入到蒸汽涡轮机12。 给水回路28,30从热回收蒸汽发生器121吸入给水并且与雾化空气冷却器18以热交换关系连通以加热给水。 给水回路28,30将加热的给水连通到热回收蒸汽发生器121的调温系统。

    ADDITIVE MANUFACTURED FUEL NOZZLE CORE FOR A GAS TURBINE ENGINE
    10.
    发明公开
    ADDITIVE MANUFACTURED FUEL NOZZLE CORE FOR A GAS TURBINE ENGINE 审中-公开
    添加剂GEFERTIGTERBRENNSTOFFDÜSENKERNFÜREINEN GASTURBINENMOTOR

    公开(公告)号：EP3052784A4

    公开(公告)日：2016-08-10

    申请号：EP14851160

    申请日：2014-10-01

    申请人： UNITED TECHNOLOGIES CORP

    发明人： XU JINQUAN

    IPC分类号： F02C7/22 ,  B22C9/10 ,  B22D17/20 ,  F23D11/38 ,  F23R3/28

    CPC分类号： B22C9/10 ,  B22C9/103 ,  B22C9/24 ,  B22D17/20 ,  F02C7/2365 ,  F05D2230/211 ,  F05D2230/30 ,  F23D11/38 ,  F23R3/28 ,  F23R3/286

    摘要： A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component. An additively manufactured sacrificial core for a fuel component of a gas turbine engine combustor includes a first structure and a second structure. The first structure at least partially defines a first passage of the fuel component. The second structure at least partially defines a second passage of the fuel component. The second structure at least partially surrounds the first structure.

    摘要翻译： 制造用于燃气涡轮发动机燃烧器的燃料部件的方法包括：添加剂制造牺牲性核心，并且至少部分地围绕所述牺牲型芯制造燃料部件主体。 牺牲芯至少部分地被去除以至少部分地限定燃料部件的内部几何形状。 用于燃气涡轮发动机燃烧器的燃料部件的附加制造的牺牲芯包括第一结构和第二结构。 第一结构至少部分地限定燃料部件的第一通道。 第二结构至少部分地限定燃料部件的第二通道。 第二结构至少部分地围绕第一结构。