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    NACELLE VENTILATION MANIFOLD
    1.
    发明申请
    NACELLE VENTILATION MANIFOLD 审中-公开
    通风通风口

    公开(公告)号：WO2015122992A1

    公开(公告)日：2015-08-20

    申请号：PCT/US2015/011944

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  PAPA, Federico

    IPC: F02C7/18 ,  F02C7/32

    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: 燃气涡轮发动机包括核心发动机壳体。 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。

    GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM
    2.
    发明申请
    GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM 审中-公开
    燃气涡轮发动机与齿轮涡轮和油热管理系统

    公开(公告)号：WO2013154637A1

    公开(公告)日：2013-10-17

    申请号：PCT/US2013/021794

    申请日：2013-01-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： PHILLIPS, Kathleen R. ,  PHILLIPS, Thomas G. ,  STEARNS, Ethan K. ,  PAPA, Federico

    IPC: F02C7/06

    CPC classification number: F01D25/20 ,  F01D25/18 ,  F01M5/002 ,  F02C7/06 ,  F02C7/14 ,  F02K9/64 ,  F05D2260/213 ,  F05D2260/40311 ,  Y02T50/676

    Abstract: A lubricant supply system for a gas turbine engine has a lubricant lube pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear for an associated gas turbine engine. A method and apparatus are disclosed.

    Abstract translation: 用于燃气涡轮发动机的润滑剂供应系统具有将润滑剂输送到出口管线的润滑剂润滑剂泵。 出口管线被分成至少一个热管线并进入冷却管线，热管线主要指向与不用于接收较冷润滑剂的发动机相关联的位置，并且冷管线通过一个或多个热交换器 哪种润滑剂被冷却。 然后，冷却管线被路由到用于相关联的燃气涡轮发动机的风扇驱动齿轮。 公开了一种方法和装置。

    GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM
    4.
    发明申请
    GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM 审中-公开
    气体涡轮发动机热管理系统

    公开(公告)号：WO2014164397A1

    公开(公告)日：2014-10-09

    申请号：PCT/US2014/022288

    申请日：2014-03-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： PAPA, Federico ,  PHILLIPS, Thomas G. ,  PHILLIPS, Kathleen R. ,  STEARNS, Ethan K. ,  HEISS, Justin W.

    IPC: F02C1/00

    CPC classification number: F02C7/14 ,  F02C7/18 ,  F02C7/224 ,  F05D2260/213 ,  F05D2270/303 ,  F05D2270/3062

    Abstract: A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的热管理系统尤其包括热交换器和阀，其控制通过热交换器A连通的第一流体的量第一传感器感测到 第二流体的第一特征，其通过热交换器连通以与第一流体交换热量，第二传感器感测第二流体的第二特性。 阀的定位基于第一特征和第二特性中的至少一个。

    VENTILATION SYSTEM USING THRUST REVERSER LINKAGES
    5.
    发明申请
    VENTILATION SYSTEM USING THRUST REVERSER LINKAGES 审中-公开
    通风系统使用颠倒性的链接

    公开(公告)号：WO2014159311A1

    公开(公告)日：2014-10-02

    申请号：PCT/US2014/022940

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： PAPA, Federico ,  VIVAR, Pilar Del Carmen

    IPC: F02K1/70 ,  F02K1/54

    CPC classification number: F02K1/70 ,  F02C6/08 ,  F02C7/18 ,  F02C9/18 ,  F02K1/72 ,  F02K1/76 ,  F05D2260/608 ,  Y02T50/675

    Abstract: A gas turbine engine includes a fan duct, an inner fixed structure, and a thrust reverser assembly. The inner fixed structure forms an inner diameter of the fan duct and encloses a core compartment. The thrust reverser assembly includes a linkage assembly mounted to the inner fixed structure within the fan duct. The linkage assembly is adapted to act as a ventilation system that allows for communication between the fan duct and the core compartment.

    Abstract translation: 燃气涡轮发动机包括风扇管道，内部固定结构和推力反向器组件。 内部固定结构形成风扇管道的内径并且包围核心隔室。 推力反向器组件包括安装到风扇管道内的内部固定结构的连杆组件。 连杆组件适于作为通风系统，其允许风扇管道和核心隔室之间的通信。

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