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    SECTIONED GAS TURBINE ENGINE DRIVEN BY SCO2 CYCLE
    2.
    发明申请
    SECTIONED GAS TURBINE ENGINE DRIVEN BY SCO2 CYCLE 审中-公开
    由SCO2循环驱动的分段气体涡轮发动机

    公开(公告)号：US20170022844A1

    公开(公告)日：2017-01-26

    申请号：US15214423

    申请日：2016-07-19

    申请人： Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

    发明人： Thomas E. Bastnagel ,  Igor Vaisman ,  Donald W. Burns ,  Michael J. Armstrong

    IPC分类号： F01K23/08 ,  F01K7/32 ,  F02C3/04 ,  F01K25/10

    CPC分类号： F01K23/08 ,  F01K7/32 ,  F01K25/103 ,  F02C1/005 ,  F02C3/04 ,  F05D2210/12 ,  F05D2210/20 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2270/09 ,  F28D7/005 ,  F28D7/0066 ,  F28D21/001 ,  F28D2021/0026 ,  F28F27/00 ,  F28F27/02 ,  F28F2265/16 ,  Y02T50/675

    摘要： An apparatus, system, and method for a gas turbine engine may include a sectioned heat exchanger. A heat exchanger may include an inlet manifold configured to receive a working fluid. A plurality of circuits including at least first and second circuits configured to transfer heat with respect to the working fluid. Each of the circuits may have a circuit inlet valve, a circuit heat exchange channel, and a circuit outlet valve. The heat exchanger may further include an outlet manifold configured to pass the working fluid to an outlet. The heat exchanger may include a first sensor configured to measure of first parameter of the first circuit and a second sensor configured to measure a second parameter of at least one of the outlet and the second circuit. A controller may be configured to selectively isolate at least one of the plurality of circuits based on a pressure difference between the first and second parameters.

    摘要翻译： 用于燃气涡轮发动机的装置，系统和方法可以包括分段热交换器。 热交换器可以包括配置成接收工作流体的入口歧管。 多个电路包括至少第一和第二电路，其被配置为相对于工作流体传递热量。 每个电路可以具有电路入口阀，回路热交换通道和电路出口阀。 热交换器还可以包括配置成使工作流体通过出口的出口歧管。 热交换器可以包括构造成测量第一电路的第一参数的第一传感器和被配置成测量出口和第二电路中的至少一个的第二参数的第二传感器。 控制器可以被配置为基于第一和第二参数之间的压力差选择性地隔离多个电路中的至少一个。

    Gas turbine engine thermally controlled flow device
    5.
    发明授权
    Gas turbine engine thermally controlled flow device 有权
    燃气涡轮发动机热控流量装置

    公开(公告)号：US09562476B2

    公开(公告)日：2017-02-07

    申请号：US14105904

    申请日：2013-12-13

    申请人： Rolls-Royce Corporation

    发明人： Thomas E. Bastnagel

    IPC分类号： F02C7/20 ,  F01D17/08 ,  F01D17/14 ,  F16K31/00 ,  G05D23/02

    CPC分类号： F02C7/20 ,  F01D17/085 ,  F01D17/141 ,  F16K31/002 ,  G05D23/022 ,  G05D23/025

    摘要： An apparatus includes a gas turbine engine flow device having an inner member and a surrounding member. The inner member has a first coefficient of thermal expansion; and the surrounding member at least partially surrounds the inner member and has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The surrounding member includes at least two walls that form a variable flow gap therebetween. The inner member is oriented relative to the at least two walls of the surrounding member such that, based on the difference in the first and second coefficients of thermal expansion, the inner member expands relatively greater than the surrounding member or the surrounding member expands relatively greater than the inner member, according to a temperature change to correspondingly enlarge or reduce the size of the variable flow gap between the at least two walls.

    摘要翻译： 一种装置包括具有内部构件和周围构件的燃气涡轮发动机流量装置。 内部构件具有第一热膨胀系数; 并且所述周围构件至少部分地围绕所述内部构件，并且具有与所述第一热膨胀系数不同的第二热膨胀系数。 周围构件包括在其间形成可变流动间隙的至少两个壁。 内部构件相对于周围构件的至少两个壁定向，使得基于第一和第二热膨胀系数的差异，内构件相对于围绕构件膨胀相对更大，或者周围构件相对更大膨胀 根据温度变化来相对地扩大或减小至少两个壁之间的可变流动间隙的尺寸。

    Gas turbine engine driven by sCO2 cycle with advanced heat rejection
    6.
    发明授权
    Gas turbine engine driven by sCO2 cycle with advanced heat rejection 有权

    公开(公告)号：US10443544B2

    公开(公告)日：2019-10-15

    申请号：US15177874

    申请日：2016-06-09

    申请人： Rolls-Royce Corporation

    发明人： Igor Vaisman ,  Thomas E. Bastnagel

    IPC分类号： F02C1/10 ,  F02K3/077 ,  F02K3/06 ,  F01K25/10 ,  F02C3/04

    摘要： A gas turbine engine includes a shaft comprising a first compressor, a fan assembly, and a power circuit that provides power to the shaft in a closed-loop system. An inner housing houses at least a portion of the shaft, the first compressor for compressing a core stream of air, and a combustor. A baffle encloses a portion of the inner housing and forms a first air passageway therebetween. A nacelle encloses a portion of the baffle and forms a second air passageway therebetween. A heat exchanger is positioned in the second air passageway that rejects heat from the power circuit into a heat rejection stream of air passing through the second air passageway. Air is accelerated as streams in parallel and via the fan assembly as the core stream into the inner housing, as a bypass flow stream of air through the first volume, and as the heat rejection stream.

    GAS TURBINE ENGINE DRIVEN BY SCO2 CYCLE WITH ADVANCED HEAT REJECTION
    7.
    发明申请
    GAS TURBINE ENGINE DRIVEN BY SCO2 CYCLE WITH ADVANCED HEAT REJECTION 审中-公开
    气体涡轮发动机由具有先进热量吸收器的SCO2循环驱动

    公开(公告)号：US20170058834A1

    公开(公告)日：2017-03-02

    申请号：US15177874

    申请日：2016-06-09

    申请人： Rolls-Royce Corporation

    发明人： Igor Vaisman ,  Thomas E. Bastnagel

    IPC分类号： F02K3/077 ,  F02K3/06

    CPC分类号： F02K3/077 ,  F01K23/10 ,  F01K25/103 ,  F02C1/10 ,  F02C3/04 ,  F02K3/06 ,  F05D2210/10 ,  F05D2220/324 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/675

    摘要： A gas turbine engine includes a shaft comprising a first compressor, a fan assembly, and a power circuit that provides power to the shaft in a closed-loop system. An inner housing houses at least a portion of the shaft, the first compressor for compressing a core stream of air, and a combustor. A baffle encloses a portion of the inner housing and forms a first air passageway therebetween. A nacelle encloses a portion of the baffle and forms a second air passageway therebetween. A heat exchanger is positioned in the second air passageway that rejects heat from the power circuit into a heat rejection stream of air passing through the second air passageway. Air is accelerated as streams in parallel and via the fan assembly as the core stream into the inner housing, as a bypass flow stream of air through the first volume, and as the heat rejection stream.

    摘要翻译： 燃气涡轮发动机包括轴，该轴包括第一压缩机，风扇组件和在闭环系统中向轴提供动力的动力回路。 内壳体容纳至少一部分轴，用于压缩核心气流的第一压缩机和燃烧器。 挡板包围内壳体的一部分并在其间形成第一空气通道。 机舱包围挡板的一部分并在其间形成第二空气通道。 热交换器位于第二空气通道中，其将来自电力回路的热量排除成通过第二空气通道的空气的排热流。 空气作为流并行并通过风扇组件作为核心流被加速进入内部壳体，作为通过第一体积的空气的旁路流，以及作为排热流。

    GAS TURBINE ENGINE THERMALLY CONTROLLED FLOW DEVICE
    8.
    发明申请
    GAS TURBINE ENGINE THERMALLY CONTROLLED FLOW DEVICE 有权
    气体涡轮发动机热控制流量装置

    公开(公告)号：US20140250899A1

    公开(公告)日：2014-09-11

    申请号：US14105904

    申请日：2013-12-13

    申请人： Rolls-Royce Corporation

    发明人： Thomas E. Bastnagel

    IPC分类号： F02C7/20

    CPC分类号： F02C7/20 ,  F01D17/085 ,  F01D17/141 ,  F16K31/002 ,  G05D23/022 ,  G05D23/025

    摘要： An apparatus includes a gas turbine engine flow device having an inner member and a surrounding member. The inner member has a first coefficient of thermal expansion; and the surrounding member at least partially surrounds the inner member and has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The surrounding member includes at least two walls that form a variable flow gap therebetween. The inner member is oriented relative to the at least two walls of the surrounding member such that, based on the difference in the first and second coefficients of thermal expansion, the inner member expands relatively greater than the surrounding member or the surrounding member expands relatively greater than the inner member, according to a temperature change to correspondingly enlarge or reduce the size of the variable flow gap between the at least two walls.

    摘要翻译： 一种装置包括具有内部构件和周围构件的燃气涡轮发动机流量装置。 内部构件具有第一热膨胀系数; 并且所述周围构件至少部分地围绕所述内部构件，并且具有与所述第一热膨胀系数不同的第二热膨胀系数。 周围构件包括在其间形成可变流动间隙的至少两个壁。 内部构件相对于周围构件的至少两个壁定向，使得基于第一和第二热膨胀系数的差异，内构件相对于围绕构件膨胀相对更大，或者周围构件相对更大膨胀 根据温度变化来相对地扩大或减小至少两个壁之间的可变流动间隙的尺寸。