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    GAS TURBINE ENGINE COOLING FLUID METERING SYSTEM
    1.
    发明申请
    GAS TURBINE ENGINE COOLING FLUID METERING SYSTEM 审中-公开
    气体涡轮发动机冷却流量计量系统

    公开(公告)号：US20160047311A1

    公开(公告)日：2016-02-18

    申请号：US14818944

    申请日：2015-08-05

    Applicant: United Technologies Corporation

    Inventor： John H. Mosley ,  Michelle Diana Stearns ,  Michael Luther Comeau ,  James P. Chasse

    IPC: F02C7/12 ,  F02C3/04

    CPC classification number: F02C7/12 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  G01F1/42 ,  Y02T50/675

    Abstract: A cooling fluid system for a gas turbine engine includes a fluid source. A turbine section includes first and second components. A fluid supply system has a primary pipe that is configured to provide a cooling supply fluid from the fluid source to a fluid fitting having a fluid junction. The fluid junction is in fluid communication with and is configured to supply a first cooling fluid to the first component. The fluid junction is in fluid communication with and is configured to supply a second cooling fluid to the second component. A flow meter is upstream from the fluid junction and is configured to receive the cooling supply fluid.

    Abstract translation: 用于燃气涡轮发动机的冷却流体系统包括流体源。 涡轮部分包括第一和第二部件。 流体供应系统具有主管，其被构造成将冷却供给流体从流体源提供到具有流体结的流体配件。 流体连接处与第一部件流体连通并且构造成将第一冷却流体供应到第一部件。 流体连接点与第二部件流体连通并且构造成将第二冷却流体供应到第二部件。 流量计位于流体接头的上游，并被配置为接收冷却供应流体。

    Gas turbine engine cooling fluid metering system
    3.
    发明授权
    Gas turbine engine cooling fluid metering system 有权

    公开(公告)号：US11939919B2

    公开(公告)日：2024-03-26

    申请号：US16439090

    申请日：2019-06-12

    Applicant: United Technologies Corporation

    Inventor： John H. Mosley ,  Michelle Diana Stearns ,  Michael Luther Comeau ,  James P. Chasse

    IPC: F02C7/12 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  G01F1/42

    CPC classification number: F02C7/12 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  G01F1/42 ,  Y02T50/60

    Abstract: A fluid supply system for a gas turbine engine includes a first component and a second component. A fluid fitting has a fluid junction. The fluid junction includes a first fluid port in fluid communication with and configured to supply a first cooling fluid to the first component. The fluid junction includes a second fluid port in fluid communication with and configured to supply a second cooling fluid to the second component. A primary pipe is fluidly connected to the fluid fitting. A flow meter is arranged upstream from the fluid junction and is configured to receive a cooling supply fluid from a fluid source. Thee flow meter is a wall having an orifice and a surface that is radiused and convex facing into the cooling supply fluid. A secondary pipe is secured to the fluid fitting and is configured to supply the second cooling fluid to the second component. A turbine section includes the first and second components. The primary pipe is configured to provide the cooling supply fluid from the fluid source to the fluid fitting.

    GAS TURBINE ENGINE COOLING FLUID METERING SYSTEM
    5.
    发明申请
    GAS TURBINE ENGINE COOLING FLUID METERING SYSTEM 审中-公开

    公开(公告)号：US20200032711A1

    公开(公告)日：2020-01-30

    申请号：US16439090

    申请日：2019-06-12

    Applicant: United Technologies Corporation

    Inventor： John H. Mosley ,  Michelle Diana Stearns ,  Michael Luther Comeau ,  James P. Chasse

    IPC: F02C7/12 ,  F01D25/12 ,  F02C7/18 ,  F02C3/04

    Abstract: A fluid supply system for a gas turbine engine includes a first component and a second component. A fluid fitting has a fluid junction. The fluid junction includes a first fluid port in fluid communication with and configured to supply a first cooling fluid to the first component. The fluid junction includes a second fluid port in fluid communication with and configured to supply a second cooling fluid to the second component. A primary pipe is fluidly connected to the fluid fitting. A flow meter is arranged upstream from the fluid junction and is configured to receive a cooling supply fluid from a fluid source. Thee flow meter is a wall having an orifice and a surface that is radiused and convex facing into the cooling supply fluid. A secondary pipe is secured to the fluid fitting and is configured to supply the second cooling fluid to the second component. A turbine section includes the first and second components. The primary pipe is configured to provide the cooling supply fluid from the fluid source to the fluid fitting.

    GAS TURBINE ENGINE TURBINE IMPELLER PRESSURIZATION
    9.
    发明申请
    GAS TURBINE ENGINE TURBINE IMPELLER PRESSURIZATION 审中-公开
    燃气涡轮发动机涡轮叶轮压缩机

    公开(公告)号：US20160003166A1

    公开(公告)日：2016-01-07

    申请号：US14769591

    申请日：2014-03-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： John H. Mosley ,  James P. Chrisikos ,  Roger Gates ,  John J. O'Connor ,  Charles C. Wu ,  David Glasspoole

    IPC: F02C9/18 ,  F01D5/08 ,  F02C7/18

    CPC classification number: F02C9/18 ,  F01D5/082 ,  F02C7/18 ,  F05D2220/3215 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

    Abstract translation: 用于燃气涡轮发动机涡轮部分的冷却系统包括支撑具有冷却通道的叶片的转子。 盘相对于转子固定，并且在转子和盘之间形成空腔。 排气源与空腔流体连通。 在空腔内布置有叶轮。 叶轮被构造成增加空腔内的流体压力以驱使排放空气源的排出空气，从而向冷却通道提供加压的冷却流体。

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