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33 条记录 (耗时 0.027 秒)

    COMBUSTOR SYSTEM FOR USE IN TURBINE ENGINES AND METHODS OF OPERATING A TURBINE ENGINE
    3.
    发明申请
    COMBUSTOR SYSTEM FOR USE IN TURBINE ENGINES AND METHODS OF OPERATING A TURBINE ENGINE 有权
    涡轮发动机中使用的燃烧器系统和运行涡轮发动机的方法

    公开(公告)号：US20130167545A1

    公开(公告)日：2013-07-04

    申请号：US13340229

    申请日：2011-12-29

    申请人： Ahmed Mostafa Elkady ,  Christian Lee Vandervort ,  Narendra Joshi ,  Sherif Mohamed

    发明人： Ahmed Mostafa Elkady ,  Christian Lee Vandervort ,  Narendra Joshi ,  Sherif Mohamed

    IPC分类号： F02C9/26 ,  F23R3/28 ,  F23R3/16

    CPC分类号： F23N5/003 ,  F02C3/14 ,  F02C3/16 ,  F02C3/20 ,  F02C9/16 ,  F23N2041/20 ,  F23R3/34 ,  F23R2900/03341

    摘要： A combustor system for use in a turbine engine is provided. The turbine engine includes turbine assembly that includes a fluid inlet, a fluid outlet, and a combustion gas path defined therebetween. The combustor system includes a first combustor assembly and a second combustor assembly. The first combustor assembly is coupled to the turbine assembly for channeling a first flow of combustion gases through the turbine assembly. The first combustor assembly is oriented adjacent to the turbine assembly inlet to channel the first flow of combustion gases to the turbine assembly through the turbine assembly inlet. The second combustor assembly is coupled to the turbine assembly along the combustion gas path for channeling a second flow of combustion gases through the turbine assembly.

    摘要翻译： 提供了一种用于涡轮发动机的燃烧器系统。 涡轮发动机包括涡轮组件，其包括流体入口，流体出口和在其间限定的燃烧气体路径。 燃烧器系统包括第一燃烧器组件和第二燃烧器组件。 第一燃烧器组件联接到涡轮机组件，用于将第一燃烧气体流引导通过涡轮组件。 第一燃烧器组件被定向成邻近涡轮机组件入口，以将第一燃烧气体流通过涡轮机组件入口引导到涡轮组件。 第二燃烧器组件沿着燃烧气体路径联接到涡轮组件，用于将第二燃烧气体流引导通过涡轮组件。

    SYSTEM AND METHOD FOR PREMIXER WAKE AND VORTEX FILLING FOR ENHANCED FLAME-HOLDING RESISTANCE
    6.
    发明申请
    SYSTEM AND METHOD FOR PREMIXER WAKE AND VORTEX FILLING FOR ENHANCED FLAME-HOLDING RESISTANCE 有权
    用于增强火焰保护电阻的预热器和VORTEX填充的系统和方法

    公开(公告)号：US20120131923A1

    公开(公告)日：2012-05-31

    申请号：US12956187

    申请日：2010-11-30

    申请人： Ahmed Mostafa ELKady ,  Christian Lee Vandervort ,  Kishore Ramakrishnan

    发明人： Ahmed Mostafa ELKady ,  Christian Lee Vandervort ,  Kishore Ramakrishnan

    IPC分类号： F23R3/28

    CPC分类号： F23R3/14 ,  F23D2900/14021 ,  F23R3/12 ,  F23R3/286

    摘要： A combustion system premixer includes one or more streamwise vortex generators configured to passively redirect surrounding high velocity air into at least one of wake and vortex regions within a combustion system fuel nozzle in response to air passing through the premixer. The streamwise vortex generators operate to minimize turbulent flow structures, thus improving air/fuel mixing, and enhancing resistance to flame-holding and flash-back within the premixer.

    摘要翻译： 燃烧系统预混合器包括一个或多个流向涡流发生器，其被配置为响应于通过预混合器的空气而将周围的高速空气被动地重定向到燃烧系统燃料喷嘴内的尾流和涡流区域中的至少一个。 流式涡流发生器用于使湍流结构最小化，从而改善空气/燃料混合，以及提高预混合器内火焰保持和闪回的抵抗力。

    Fuel nozzle and assembly and gas turbine comprising the same
    8.
    发明授权
    Fuel nozzle and assembly and gas turbine comprising the same 有权
    包括其的燃料喷嘴和组件以及燃气轮机

    公开(公告)号：US09557050B2

    公开(公告)日：2017-01-31

    申请号：US12847688

    申请日：2010-07-30

    申请人： Christian Lee Vandervort ,  Joel Meier Haynes

    发明人： Christian Lee Vandervort ,  Joel Meier Haynes

    IPC分类号： F02C3/00 ,  F23C6/04 ,  F23D11/38 ,  F23D14/48 ,  F23R3/04 ,  F23R3/14 ,  F23R3/28

    CPC分类号： F23C6/045 ,  F23D11/38 ,  F23D14/48 ,  F23R3/04 ,  F23R3/14 ,  F23R3/28

    摘要： A nozzle for assemblies and gas turbines is provided. The nozzle exhibits destabilized flame holding characteristics, i.e., the nozzle is unable to stabilize flame up to an equivalence ratio of about 0.65. As a result, flame heat release is delayed resulting in lower peak flame temperatures and correspondingly lower NOx levels. Flame stabilization capability is retained for higher equivalence ratios to support operation of the combustor in other regions of the load range.

    摘要翻译： 提供了用于组件和燃气轮机的喷嘴。 喷嘴表现出不稳定的火焰保持特性，即喷嘴不能将火焰稳定至约0.65的当量比。 结果，火焰放热被延迟，导致较低的峰值火焰温度和相应降低的NOx水平。 保持火焰稳定能力以获得更高的当量比，以支持在负载范围的其他区域的燃烧器的操作。

    Pulse detonation engine bypass and cooling flow with downstream mixing volume
    9.
    发明授权
    Pulse detonation engine bypass and cooling flow with downstream mixing volume 失效
    脉冲爆震发动机旁路和冷却流量与下游混合量

    公开(公告)号：US07841167B2

    公开(公告)日：2010-11-30

    申请号：US11561155

    申请日：2006-11-17

    申请人： Adam Rasheed ,  Anthony John Dean ,  Peirre Francois Pinard ,  Christian Lee Vandervort ,  Venkat Eswarlu Tangirala

    发明人： Adam Rasheed ,  Anthony John Dean ,  Peirre Francois Pinard ,  Christian Lee Vandervort ,  Venkat Eswarlu Tangirala

    IPC分类号： F02K5/02

    CPC分类号： F02C5/11 ,  F02C5/02 ,  F02K7/04

    摘要： An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct.

    摘要翻译： 发动机包含至少一个脉冲爆震燃烧器，其被旁路气流导管包围，旁路气流通过旁路气流引导。 旁路空气管道包含至少一个会聚发散结构，以阻尼或阻塞来自脉冲爆震燃烧器的冲击波的上游传播通过旁路流动空气管道。 旁路空气还用于冷却脉冲爆震燃烧器的外表面。 旁路空气流与PDC的放热一起控制，以向下游能量转换装置（例如涡轮机）提供适当量的热能。 混合气室位于脉冲爆震燃烧器和旁路流动空气管道的下游。

    PULSE DETONATION ENGINE BYPASS AND COOLING FLOW WITH DOWNSTREAM MIXING VOLUME
    10.
    发明申请
    PULSE DETONATION ENGINE BYPASS AND COOLING FLOW WITH DOWNSTREAM MIXING VOLUME 失效
    脉冲爆震发动机旁路和冷却流量与下游混合体积

    公开(公告)号：US20080115480A1

    公开(公告)日：2008-05-22

    申请号：US11561155

    申请日：2006-11-17

    申请人： Adam Rasheed ,  Anthony John Dean ,  Pierre Francois Pinard ,  Christian Lee Vandervort ,  Venkat Eswarlu Tangirala

    发明人： Adam Rasheed ,  Anthony John Dean ,  Pierre Francois Pinard ,  Christian Lee Vandervort ,  Venkat Eswarlu Tangirala

    IPC分类号： F02C5/00

    CPC分类号： F02C5/11 ,  F02C5/02 ,  F02K7/04

    摘要： An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct.

    摘要翻译： 发动机包含至少一个脉冲爆震燃烧器，其被旁路气流导管包围，旁路气流通过旁路气流引导。 旁路空气管道包含至少一个会聚发散结构，以阻尼或阻塞来自脉冲爆震燃烧器的冲击波的上游传播通过旁路流动空气管道。 旁路空气还用于冷却脉冲爆震燃烧器的外表面。 旁路空气流与PDC的放热一起控制，以向下游能量转换装置（例如涡轮机）提供适当量的热能。 混合气室位于脉冲爆震燃烧器和旁路流动空气管道的下游。