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    PLATFORM WITH CURVED EDGES ADJACENT SUCTION SIDE OF AIRFOIL
    11.
    发明申请
    PLATFORM WITH CURVED EDGES ADJACENT SUCTION SIDE OF AIRFOIL 审中-公开
    具有弯曲边缘的平台，AIRFOIL附近相邻侧

    公开(公告)号：WO2014105102A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/025738

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F01D5/14 ,  F01D5/30 ,  F01D25/00 ,  F02C7/00

    CPC classification number: F01D5/147 ,  F01D5/021 ,  F01D5/143 ,  F01D5/145 ,  F01D9/02 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/80 ,  Y02T50/673

    Abstract: A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge adjacent the suction side and a second curved edge spaced from the pressure side such that more than half of the platform is located to the pressure side. The platform located to the pressure side has a non-axisymmetrical surface contouring.

    Abstract translation: 燃气涡轮发动机部件包括翼型件和平台。 翼型件具有压力侧和相对的吸力侧。 平台连接到翼型件，并且具有邻近吸力侧的第一弯曲边缘和与压力侧间隔开的第二弯曲边缘，使得平台的一半以上位于压力侧。 位于压力侧的平台具有非轴对称的表面轮廓。

    TRAILING EDGE AND TIP COOLING
    12.
    发明申请
    TRAILING EDGE AND TIP COOLING 审中-公开
    跟踪边缘和提示冷却

    公开(公告)号：WO2014085020A1

    公开(公告)日：2014-06-05

    申请号：PCT/US2013/067805

    申请日：2013-10-31

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F01D5/18 ,  F02C7/12

    CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2250/38 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A gas turbine engine component includes an airfoil extending radially from a root section to a tip section and having a trailing edge cooling passageway and first, second and third flow dividers in the cooling passageway. The first, second and third flow dividers have longitudinal axes that are angled based upon a position of the flow divider relative to the tip section of the airfoil.

    Abstract translation: 燃气涡轮发动机部件包括从根部向顶端部分径向延伸的翼型件，并且具有后缘冷却通道和冷却通道中的第一，第二和第三分流器。 第一，第二和第三分流器具有基于分流器相对于翼型件的末端部分的位置成角度的纵向轴线。

    ADDITIVE MANUFACTURED FUEL NOZZLE CORE FOR A GAS TURBINE ENGINE
    15.
    发明申请
    ADDITIVE MANUFACTURED FUEL NOZZLE CORE FOR A GAS TURBINE ENGINE 审中-公开
    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：WO2015050987A1

    公开(公告)日：2015-04-09

    申请号：PCT/US2014/058617

    申请日：2014-10-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F02C7/22 ,  F23R3/28 ,  F23D11/38 ,  B22D17/20 ,  B22C9/10

    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：添加剂制造牺牲芯，并且至少部分地围绕所述牺牲芯制造燃料部件主体。 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。 一种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。

    AIRFOIL MEMBER AND COMPOSITE PLATFORM HAVING CONTOURED ENDWALL
    18.
    发明申请
    AIRFOIL MEMBER AND COMPOSITE PLATFORM HAVING CONTOURED ENDWALL 审中-公开
    AIRFOIL会员和具有轮廓终端的复合平台

    公开(公告)号：WO2014099102A1

    公开(公告)日：2014-06-26

    申请号：PCT/US2013/063432

    申请日：2013-10-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F01D5/30 ,  F01D11/00 ,  F02C7/00 ,  F02K3/00

    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。

    MULTI-LOBED COOLING HOLE ARRAY
    19.
    发明申请
    MULTI-LOBED COOLING HOLE ARRAY 审中-公开
    多出口冷却孔阵列

    公开(公告)号：WO2013165508A2

    公开(公告)日：2013-11-07

    申请号：PCT/US2013/025710

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F02C7/18 ,  F01D25/12 ,  F02K3/00 ,  F01D5/08

    CPC classification number: F01D5/186 ,  F05D2250/324 ,  F05D2250/52 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/676 ,  Y10T29/49323

    Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and first and second cooling holes extending through the wall. The first and second cooling holes each include an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. Each diffusing section includes first and second lobes, each lobe diverging longitudinally and laterally from the metering section. The outlets of each cooling hole include first and second lateral ends and a trailing edge. One of the lateral ends of the outlet of the first cooling hole and one of the lateral ends of the outlet of the second cooling hole meet upstream of the trailing edge of the first cooling hole and the trailing edge of the second cooling hole.

    Abstract translation: 燃气涡轮发动机部件包括具有第一和第二壁表面以及延伸穿过该壁的第一和第二冷却孔的壁。 第一和第二冷却孔各自包括位于第一壁表面处的入口，位于第二壁表面处的出口，从入口向下游延伸的计量部分以及从计量部分延伸至出口的扩散部分。 每个扩散部分包括第一和第二凸角，每个凸角从计量部分纵向和横向发散。 每个冷却孔的出口包括第一和第二横向端以及后缘。 第一冷却孔的出口的一个侧端和第二冷却孔的出口的一个侧端在第一冷却孔的后缘和第二冷却孔的后缘的上游汇合。 p>

    COOLING HOLE WITH ENHANCED FLOW ATTACHMENT
    20.
    发明申请
    COOLING HOLE WITH ENHANCED FLOW ATTACHMENT 审中-公开

    公开(公告)号：WO2013165503A3

    公开(公告)日：2013-11-07

    申请号：PCT/US2013/025684

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan ,  LEVASSEUR, Glenn

    IPC: F02C7/18 ,  F01D25/12 ,  F02K3/00 ,  F01D5/08

    Abstract: A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall 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 a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet.

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