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    VARIABLE THICKNESS TRAILING EDGE CAVITY AND METHOD OF MAKING
    2.
    发明申请
    VARIABLE THICKNESS TRAILING EDGE CAVITY AND METHOD OF MAKING 审中-公开
    可变厚度跟踪边缘和制作方法

    公开(公告)号：WO2014165337A1

    公开(公告)日：2014-10-09

    申请号：PCT/US2014/031472

    申请日：2014-03-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F01D5/14 ,  F01D5/18 ,  B22F5/04 ,  B22F3/105

    CPC classification number: F01D5/282 ,  B22C9/101 ,  B22C9/103 ,  B22D25/02 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F5/10 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/13 ,  F05D2230/14 ,  F05D2230/21 ,  F05D2230/60 ,  F05D2240/304 ,  F05D2250/182 ,  F05D2260/202 ,  F05D2300/13 ,  F05D2300/20 ,  Y02P10/292 ,  Y02P10/295

    Abstract: A method for forming an airfoil includes forming a ceramic core, forming a refractory metal core using additive manufacturing, joining the ceramic core and the refractory metal core to form a hybrid core, and casting the airfoil around the hybrid core. The ceramic core is used to define an internal cavity of the airfoil. The refractory metal core has an upstream end and a downstream end. The upstream end has a lateral thickness greater than a lateral thickness of the downstream end. The refractory metal core is used to define a trailing edge cavity within the airfoil. The trailing edge cavity is in flow communication with the internal cavity of the airfoil and trailing edge slots located on an outer surface of the airfoil near a trailing edge. This method provides for an airfoil having a trailing edge cavity of variably thickness and casting cores used for their manufacture.

    Abstract translation: 一种用于形成翼型的方法包括形成陶瓷芯，使用添加剂制造形成耐火金属芯，将陶瓷芯和难熔金属芯接合以形成混合芯，并将翼型铸造在混合型芯周围。 陶瓷芯用于限定翼型的内腔。 难熔金属芯具有上游端和下游端。 上游端具有大于下游端的横向厚度的横向厚度。 难熔金属芯用于限定翼型内的后缘腔。 后缘空腔与位于翼缘的外表面附近的翼型件和后边缘槽的内部空腔流动连通。 该方法提供了具有可变厚度的后缘腔和用于其制造的铸芯的翼型件。

    GAS TURBINE ENGINE HAVING A MISTUNED STAGE
    3.
    发明申请
    GAS TURBINE ENGINE HAVING A MISTUNED STAGE 审中-公开
    具有混合阶段的气体涡轮发动机

    公开(公告)号：WO2014130332A1

    公开(公告)日：2014-08-28

    申请号：PCT/US2014/016173

    申请日：2014-02-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan ,  TENNEY, Frederic, Tisdall

    IPC: F01D5/04 ,  F02C7/00

    CPC classification number: F02C3/06 ,  F01D5/143 ,  F01D5/16 ,  F04D29/542 ,  F04D29/547 ,  F04D29/661 ,  F04D29/666 ,  F05D2260/961 ,  Y02T50/673

    Abstract: A stage of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a row of flow directing components circumferentially disposed about a centerline axis and at least one flow directing component of the row having at least one design characteristic that is dissimilar from a corresponding design characteristic of at least one other flow directing component of the row.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机的一个阶段尤其包括围绕中心线轴线周向设置的一排流动引导部件，以及具有至少一个设计特征的行的至少一个流动引导部件 其与行的至少一个其它流动指向部件的相应设计特征不同。

    GAS TURBINE ENGINE COMPONENT WITH CUSPED, LOBED COOLING HOLE
    6.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH CUSPED, LOBED COOLING HOLE 审中-公开

    公开(公告)号：WO2013165518A9

    公开(公告)日：2013-11-07

    申请号：PCT/US2013/025879

    申请日：2013-02-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

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

    Abstract: A component for a gas turbine engine includes a wall and a cooling hole. The wall has a first surface and a second surface. The second surface is exposed to hot gas flow. The cooling hole extends through the wall. The cooling hole includes a metering section extending from an inlet in the first surface of the wall to a transition, a diffusing section extending from the transition to an outlet in the second surface of the wall, a cusp on the transition, and a first longitudinal ridge extending along the diffusing section between the transition and the outlet. The first longitudinal ridge divides the diffusing section into first and second lobes.

    GAS TURBINE ENGINE COMPONENT WITH IMPINGEMENT AND LOBED COOLING HOLE
    7.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH IMPINGEMENT AND LOBED COOLING HOLE 审中-公开
    气动涡轮发动机组件与冲击和滚动冷却孔

    公开(公告)号：WO2013123120A1

    公开(公告)日：2013-08-22

    申请号：PCT/US2013/026040

    申请日：2013-02-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F01D5/18 ,  F01D25/12 ,  F02C7/12

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a gas path wall having a first and second opposing surfaces and a baffle positioned along the gas path wall. The baffle has impingement holes for directing cooling fluid onto the first surface of the gas path wall. A cooling hole is formed in the gas path wall and extends from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface. A longitudinal ridge extends along the cooling hole between the transition and the outlet. The longitudinal ridge divides the diffusing section of the cooling hole into first and second lobes.

    Abstract translation: 燃气涡轮发动机部件包括具有第一和第二相对表面的气体通道壁和沿着气体路径壁定位的挡板。 挡板具有用于将冷却流体引导到气体通道壁的第一表面上的冲击孔。 在气体通道壁中形成冷却孔，并且从具有第一表面中的入口的计量部分延伸通过在第二表面中具有出口的扩散部分的过渡。 纵向脊沿着过渡段和出口之间的冷却孔延伸。 纵向脊将冷却孔的扩散部分分成第一和第二凸角。

    GAS TURBINE ENGINE HAVING MINIMUM COOLING AIRFLOW
    8.
    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：WO2015126551A1

    公开(公告)日：2015-08-27

    申请号：PCT/US2015/012122

    申请日：2015-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F02C7/18 ,  F01D25/12

    CPC classification number: F01D17/145 ,  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。

    MULTI-LOBED COOLING HOLE
    9.
    发明申请
    MULTI-LOBED COOLING HOLE 审中-公开
    多孔冷却孔

    公开(公告)号：WO2014197043A2

    公开(公告)日：2014-12-11

    申请号：PCT/US2014/023346

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, JinQuan

    IPC: F02C7/12 ,  F02C7/18 ,  F01D25/12 ,  F01D5/18 ,  F04D29/58

    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。

    PLATFORM WITH CURVED EDGES
    10.
    发明申请
    PLATFORM WITH CURVED EDGES 审中-公开
    平台与曲折边

    公开(公告)号：WO2014105103A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/025741

    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 to the suction side of the airfoil and a second curved edge to the pressure side of the airfoil. The first and second curved edges extend along a surface of the platform having a neutral elevation with respect to a reference axisymmetrical platform surface for the gas turbine engine.

    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，并且具有到翼型的吸入侧的第一弯曲边缘和到翼型的压力侧的第二弯曲边缘。 第一和第二弯曲边缘沿着平台的表面延伸，具有相对于燃气涡轮发动机的参考轴对称平台表面的中立高度。

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