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    Gas turbine engine thermal management system
    11.
    发明授权
    Gas turbine engine thermal management system 有权
    燃气轮机发动机热管理系统

    公开(公告)号：US09038397B2

    公开(公告)日：2015-05-26

    申请号：US14247575

    申请日：2014-04-08

    Applicant: United Technologies Corporation

    Inventor： Federico Papa ,  Thomas G. Phillips ,  Kathleen R. Phillips ,  Ethan K. Stearns ,  Justin W. Heiss

    IPC: F02C1/00 ,  F02C7/06 ,  F02K99/00 ,  F02C7/12 ,  F02C3/08 ,  F02C7/224 ,  F02C7/232 ,  F02C9/48 ,  G05B15/02 ,  G05D7/06

    CPC classification number: F02C7/12 ,  F01D25/12 ,  F02C3/08 ,  F02C7/06 ,  F02C7/08 ,  F02C7/14 ,  F02C7/224 ,  F02C7/232 ,  F02C9/00 ,  F02C9/48 ,  F05D2220/32 ,  F05D2260/213 ,  G05B15/02 ,  G05D7/06 ,  Y02T50/675

    Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan. A turbine section is configured for driving the geared architecture. A thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine. A first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit. A second heat exchanger is incorporated into the first fluid circuit. A valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger. A controller is configured to control a positioning of the valve. The amount of the first fluid communicated to the first heat exchanger is based on a first characteristic of a second fluid and the amount of the first fluid communicated to the second heat exchanger is based on a second characteristic of the second fluid. A method and a system are also disclosed.

    Abstract translation: 根据本公开的示例性实施例的燃气涡轮发动机以及其它可能的事情包括风扇。 齿轮架构配置为驱动风扇。 涡轮机部分被配置用于驱动齿轮架构。 一种热管理系统，其包括第一流体回路和第二流体回路，其管理在燃气涡轮发动机的至少一部分中产生的热量。 第一热交换器被并入到第一流体回路和第二流体回路的每一个中。 第二热交换器被并入到第一流体回路中。 阀门控制与第一热交换器和第二热交换器连通的第一流体的量。 控制器被配置为控制阀的定位。 与第一热交换器连通的第一流体的量基于第二流体的第一特性，并且与第二热交换器连通的第一流体的量基于第二流体的第二特性。 还公开了一种方法和系统。

    PEAK THERMAL PROTECTION OF A TURBOFAN ENGINE COMPONENT USING PHASE CHANGE MATERIAL
    16.
    发明申请
    PEAK THERMAL PROTECTION OF A TURBOFAN ENGINE COMPONENT USING PHASE CHANGE MATERIAL 审中-公开

    公开(公告)号：US20200256253A1

    公开(公告)日：2020-08-13

    申请号：US16271213

    申请日：2019-02-08

    Applicant: United Technologies Corporation

    Inventor： Nigel David Sawyers-Abbott ,  Federico Papa

    IPC: F02C7/24

    Abstract: A gas turbine engine system includes a gas turbine engine, a temperature-sensitive component, and a thermal protection structure. The gas turbine engine has an engine core that generates heat while operational and for a period after operation. The temperature-sensitive component is disposed at a component location proximate the engine core. The thermal protection structure is interposed between the temperature-sensitive component and the gas turbine-engine, and includes a phase change material (PCM) layer disposed to absorb a transient heat spike from the engine core.

    NACELLE VENTILATION MANIFOLD
    18.
    发明申请
    NACELLE VENTILATION MANIFOLD 审中-公开

    公开(公告)号：US20180363492A1

    公开(公告)日：2018-12-20

    申请号：US16059377

    申请日：2018-08-09

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Federico Papa

    IPC: F01D17/14 ,  F02C3/04 ,  F02C9/18 ,  F02C7/18 ,  F01D25/26

    Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

    NACELLE VENTILATION MANIFOLD
    20.
    发明申请
    NACELLE VENTILATION MANIFOLD 审中-公开
    通风通风口

    公开(公告)号：US20160333728A1

    公开(公告)日：2016-11-17

    申请号：US15111553

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Federico Papa

    IPC: F01D17/14 ,  F01D25/26 ,  F02C9/18 ,  F02C3/04 ,  F02C7/18

    CPC classification number: F01D17/145 ,  F01D25/26 ,  F02C3/04 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/608 ,  Y02T50/675

    Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

    Abstract translation: 一种燃气涡轮发动机包括一个核心发动机壳体。 机舱位于核心发动机壳体的径向外侧。 外部旁路外壳位于机舱的外侧。 至少有一个待冷却的附件定位在径向位于核心发动机壳体和机舱之间的腔室中。 歧管将冷却空气提供到腔室中，并且围绕核心发动机的中心轴线周向延伸。 机舱在圆周范围内具有不对称的流动横截面。

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