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    GAS TURBINE ENGINE HAVING MINIMUM COOLING AIRFLOW
    73.
    发明申请
    GAS TURBINE ENGINE HAVING MINIMUM COOLING AIRFLOW 审中-公开
    具有最小冷却气流的气体涡轮发动机

    公开(公告)号：US20160326903A1

    公开(公告)日：2016-11-10

    申请号：US15111531

    申请日：2015-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan Xu

    IPC: F01D17/14 ,  F01D11/00 ,  F02C7/14 ,  F02C9/18 ,  F02C3/04 ,  F02C7/18

    CPC classification number: F01D17/145 ,  B64D2033/024 ,  F01D11/003 ,  F01D17/105 ,  F01D25/12 ,  F02C3/04 ,  F02C7/14 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2300/514 ,  Y02T50/675

    Abstract: A cooling system for a gas turbine engine comprises a passage capable of receiving cooling air, a compartment radially adjacent thereto and axially aligned therewith, an opening therebetween, a valve within the opening, and a heat exchanger received in the compartment. The valve is moveable between a maximum open position and a minimum open position for increasing or decreasing airflow from the passage into the compartment. At the valve minimum open position, a leakage path is provided between the passage and the compartment, whereby cooling air is capable of passing from the passage to the compartment and toward the heat exchanger at all valve positions. A gas turbine engine is also disclosed.

    Abstract translation: 用于燃气涡轮发动机的冷却系统包括能够接收冷却空气的通道，与其径向相邻并与其轴向对准的室，其间的开口，开口内的阀和容纳在隔室中的热交换器。 阀可在最大打开位置和最小打开位置之间移动，以增加或减少从通道进入隔室的气流。 在阀门最小打开位置，在通道和隔室之间设置泄漏路径，由此冷却空气能够在所有阀位置从通道通向隔室并且朝向热交换器。 还公开了一种燃气涡轮发动机。

    ADDITIVE MANUFACTURED FUEL NOZZLE CORE FOR A GAS TURBINE ENGINE
    75.
    发明申请
    ADDITIVE MANUFACTURED FUEL NOZZLE CORE FOR A GAS TURBINE ENGINE 有权
    用于燃气涡轮发动机的添加剂制造燃料喷嘴芯

    公开(公告)号：US20160236271A1

    公开(公告)日：2016-08-18

    申请号：US15026409

    申请日：2014-10-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan Xu

    IPC: B22C9/10 ,  F23R3/28 ,  B22C9/24

    CPC classification number: B22C9/10 ,  B22C9/103 ,  B22C9/24 ,  B22D17/20 ,  F02C7/2365 ,  F05D2230/211 ,  F05D2230/30 ,  F23D11/38 ,  F23R3/28 ,  F23R3/286

    Abstract: A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component. An additively manufactured sacrificial core for a fuel component of a gas turbine engine combustor includes a first structure and a second structure. The first structure at least partially defines a first passage of the fuel component. The second structure at least partially defines a second passage of the fuel component. The second structure at least partially surrounds the first structure.

    Abstract translation: 一种制造用于燃气涡轮发动机燃烧器的燃料部件的方法包括添加剂制造牺牲性核心并且至少部分地围绕所述牺牲性核心制造燃料部件主体。 牺牲芯至少部分地被去除以至少部分地限定燃料部件的内部几何形状。 用于燃气涡轮发动机燃烧器的燃料部件的附加制造的牺牲芯包括第一结构和第二结构。 第一结构至少部分地限定燃料部件的第一通道。 第二结构至少部分地限定燃料部件的第二通道。 第二结构至少部分地围绕第一结构。

    Film cooling channel array having anti-vortex properties
    77.
    发明授权
    Film cooling channel array having anti-vortex properties 有权
    具有防涡流特性的薄膜冷却通道阵列

    公开(公告)号：US09316104B2

    公开(公告)日：2016-04-19

    申请号：US13660148

    申请日：2012-10-25

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: F28F3/12 ,  F01D5/18 ,  F01D9/06 ,  F23R3/00

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A cooling channel array carried by a component wall of a gas turbine engine is provided. The cooling channel array comprises a diffusion cavity and a metering section. The metering section comprises a main hole and two or more side holes. The side holes may be separate from the main hole or may branch off of the main hole. The diffusion cavity may incorporate a lobed configuration to help diffuse cooling fluid as it exits the cooling channel array.

    Abstract translation: 提供了由燃气涡轮发动机的部件壁承载的冷却通道阵列。 冷却通道阵列包括扩散腔和计量部。 计量部分包括主孔和两个或更多个侧孔。 侧孔可以与主孔分离，或者可以从主孔分支。 扩散腔可以包括叶形结构，以帮助冷却流体在离开冷却通道阵列时扩散。

    MULTI-LOBED COOLING HOLE
    78.
    发明申请
    MULTI-LOBED COOLING HOLE 审中-公开
    多孔冷却孔

    公开(公告)号：US20160024937A1

    公开(公告)日：2016-01-28

    申请号：US14775015

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan Xu

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/73 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first surface, an outlet located at the second surface, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and having a first downstream end adjacent the outlet and spaced from the inlet by a first distance, a second lobe diverging longitudinally from the metering section and having a second downstream end adjacent the outlet and spaced from the inlet by a second distance different from the first, and a transition region positioned between the lobes, the transition region having a third downstream end adjacent the outlet.

    Abstract translation: 经受高温气体流动的燃气涡轮发动机部件包括具有第一和第二表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一表面处的入口，位于第二表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括从计量部分纵向和横向分开的第一凸角，并且具有邻近出口并与入口间隔第一距离的第一下游端，与计量部分纵向分开的第二凸角，并且具有相邻的第二下游端 出口并且与入口间隔开不同于第一距离的第二距离，以及位于叶片之间的过渡区域，过渡区域具有邻近出口的第三下游端。

    Airfoil Member and Composite Platform Having Contoured Endwall
    80.
    发明申请
    Airfoil Member and Composite Platform Having Contoured Endwall 有权
    翼型构件和具有轮廓端壁的复合平台

    公开(公告)号：US20140212292A1

    公开(公告)日：2014-07-31

    申请号：US13718181

    申请日：2012-12-18

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: F01D5/30 ,  F01D5/28

    CPC classification number: F01D5/30 ,  F01D5/143 ,  F01D5/145 ,  F01D5/282 ,  F01D5/284 ,  F01D5/3084 ,  F01D5/3092 ,  F05D2240/80 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49316

    Abstract: An airfoil member and platform assembly for a gas turbine engine is provided. The platform to which the airfoil member is anchored is made of a composite material and includes an endwall defining a contoured region for improved aerodynamics. The contoured region influences the flow of gases through the flow passages between the airfoil members, thereby reducing endwall losses due to horseshoe vortexing. The composite material may be woven ceramic matrix composite fibers infiltrated with a ceramic matrix material or woven organic matrix composite fibers infiltrated with an organic matrix material.

    Abstract translation: 提供了一种用于燃气涡轮发动机的翼型件和平台组件。 机翼构件锚固的平台由复合材料制成，并且包括限定用于改善空气动力学的轮廓区域的端壁。 轮廓区域影响通过翼型构件之间的流动通道的气体流动，从而减少由于马蹄涡旋引起的端壁损失。 复合材料可以是用陶瓷基体材料或有机基质材料渗透的机织有机基质复合纤维渗透的编织陶瓷基复合纤维。

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