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    Multi-circuit lubrication system for a turbine engine
    1.
    发明授权
    Multi-circuit lubrication system for a turbine engine 有权

    公开(公告)号：US11053815B2

    公开(公告)日：2021-07-06

    申请号：US14765211

    申请日：2014-02-04

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Simon Pickford

    IPC: F01D25/20 ,  F02C7/14 ,  F02C3/107 ,  F01D25/18 ,  F01D25/12 ,  F01D1/02 ,  F01D15/10 ,  F01D15/12 ,  F01D25/08 ,  F01D25/16

    Abstract: A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger, wherein the second lubricant circuit is fluidly separate from the first lubricant circuit. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second turbine engine component includes a bearing. The shaft is supported by the bearing and connected to one of the engine stages.

    Low profile compressor bleed air-oil coolers
    3.
    发明授权
    Low profile compressor bleed air-oil coolers 有权

    公开(公告)号：US09714610B2

    公开(公告)日：2017-07-25

    申请号：US13645067

    申请日：2012-10-04

    Applicant: United Technologies Corporation

    Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Simon Pickford ,  Allan R. Penda

    IPC: F02C7/14 ,  F02C6/08

    CPC classification number: F02C6/08 ,  F02C7/14 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/675

    Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

    DIFFUSER MOUNTED FUEL-AIR HEAT EXCHANGER
    4.
    发明申请
    DIFFUSER MOUNTED FUEL-AIR HEAT EXCHANGER 审中-公开

    公开(公告)号：US20170167385A1

    公开(公告)日：2017-06-15

    申请号：US14963545

    申请日：2015-12-09

    Applicant: United Technologies Corporation

    Inventor： James D. Hill ,  Steven J. Laporte ,  Wendell V. Twelves, JR. ,  Stephen K. Kramer ,  Simon Pickford

    IPC: F02C7/18

    CPC classification number: F02C7/141 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the heat exchanger via a fuel pipe and toward a fuel nozzle of the combustor. An airflow inlet directs a cooling airflow through the heat exchanger to reduce an airflow temperature via thermal energy exchange between the cooling airflow and the flow of fuel. An airflow outlet directs the cooling airflow from the heat exchanger toward one or more of components of the turbine to cool the one or more components.

    Air-Oil Heat Exchangers with Minimum Bypass Flow Pressure Loss
    7.
    发明申请
    Air-Oil Heat Exchangers with Minimum Bypass Flow Pressure Loss 审中-公开
    具有最小旁路流量压力损失的空气 - 油热交换器

    公开(公告)号：US20150361891A1

    公开(公告)日：2015-12-17

    申请号：US14765509

    申请日：2013-12-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Simon Pickford

    IPC: F02C7/18 ,  F02C7/04 ,  F01D25/24 ,  F02C3/04

    Abstract: A geared turbofan engine having a bypass ratio of at least six (6) includes a nacelle that encloses a fan assembly and at least part of an engine case that houses an engine core. The fan assembly is disposed fore of the engine case. The nacelle and engine case defining an annular fan duct for air flow that passes through the fan but that bypasses the engine core. The nacelle includes a fore end and an aft end that defines a fan nozzle with the engine case. The engine case includes an inlet and an outlet. The inlet is connected to a duct that extends within the engine case to the outlet. The duct accommodates an air-oil heat exchanger between the inlet and outlet of the duct, which may be used for the gearbox dedicated to reducing the speed of the fan as compared to the low pressure turbine.

    Abstract translation: 具有至少六（6）的旁路比的齿轮涡扇发动机包括包围风扇组件和容纳发动机芯的发动机壳体的至少一部分的机舱。 风扇组件设置在发动机壳体的前方。 机舱和发动机壳体限定了通过风扇但绕过发动机芯的空气流的环形风扇通道。 机舱包括前端和后端，其与发动机壳体形成风扇喷嘴。 发动机壳体包括入口和出口。 入口连接到在发动机壳体内延伸到出口的管道。 管道容纳在管道的入口和出口之间的空气 - 油热交换器，其可用于与低压涡轮机相比专用于降低风扇速度的变速箱。

    Multi-circuit lubrication system for a turbine engine
    8.
    发明授权
    Multi-circuit lubrication system for a turbine engine 有权

    公开(公告)号：US10605104B2

    公开(公告)日：2020-03-31

    申请号：US14765217

    申请日：2014-02-04

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Simon Pickford

    IPC: F01D9/06 ,  F01D25/18 ,  F02C7/06 ,  F02C7/14

    Abstract: A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger. The second lubricant circuit is fluidly coupled with the first lubricant circuit, and the second turbine engine component includes a bearing. The shaft is supported by the bearing, and connected to one of the engine stages.

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