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    COOLING HOLE WITH ENHANCED FLOW ATTACHMENT
    51.
    发明申请
    COOLING HOLE WITH ENHANCED FLOW ATTACHMENT 审中-公开

    公开(公告)号：US20180038231A1

    公开(公告)日：2018-02-08

    申请号：US15237406

    申请日：2016-08-15

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu ,  Glenn Levasseur

    IPC: F01D5/18 ,  F01D9/06

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

    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.

    Trailing edge and tip cooling
    54.
    发明授权
    Trailing edge and tip cooling 有权
    后缘和尖端冷却

    公开(公告)号：US09482101B2

    公开(公告)日：2016-11-01

    申请号：US13687567

    申请日：2012-11-28

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: F01D5/18

    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 MANUFACTURING METHOD FOR THE ADDITION OF FEATURES WITHIN COOLING HOLES
    56.
    发明申请
    ADDITIVE MANUFACTURING METHOD FOR THE ADDITION OF FEATURES WITHIN COOLING HOLES 审中-公开
    在冷却孔中加入特征的添加剂制造方法

    公开(公告)号：US20160008889A1

    公开(公告)日：2016-01-14

    申请号：US14771436

    申请日：2014-03-11

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: B22F7/08 ,  B23K26/00 ,  B23K15/00 ,  B23K26/342 ,  F01D5/18 ,  B28B1/00

    Abstract: A method for forming a diffusion cooling hole in a substrate includes removing material from the substrate to form a metering section having an inlet on a first side of the substrate and removing material from the substrate to form a diffusing section that extends between the metering section and an outlet located on a second side of the substrate generally opposite the first side. The method also includes forming a feature on a substrate surface within one of the metering section and the diffusing section. Forming the feature includes depositing a material on the substrate surface and selectively heating the material to join the material with the substrate surface and form the feature.

    Abstract translation: 一种用于在基板中形成扩散冷却孔的方法，包括从基板移除材料以形成计量部分，该计量部分具有在基板的第一侧上的入口，并从基板移除材料以形成扩散部分，该扩散部分在计量部分和 出口位于基板的与第一侧大致相对的第二侧上。 该方法还包括在计量部分和扩散部分之一内的基板表面上形成特征。 形成特征包括在衬底表面上沉积材料并选择性地加热材料以将材料与衬底表面接合并形成特征。

    GAS TURBINE ENGINE FLUID SUPPLY SYSTEM HAVING AT LEAST ONE AIRBAG, AND METHOD FOR MAINTAINING NON-INTERRUPTED CIRCULATING TURBOMACHINE FLUID FLOW DURING A NON-POSITIVE G-FORCE EVENT
    57.
    发明申请
    GAS TURBINE ENGINE FLUID SUPPLY SYSTEM HAVING AT LEAST ONE AIRBAG, AND METHOD FOR MAINTAINING NON-INTERRUPTED CIRCULATING TURBOMACHINE FLUID FLOW DURING A NON-POSITIVE G-FORCE EVENT 有权
    具有至少一个安全气囊的气体涡轮发动机流体供应系统，以及在非正式G力量事件期间维持非中断循环涡轮流量流体的方法

    公开(公告)号：US20150345656A1

    公开(公告)日：2015-12-03

    申请号：US14724413

    申请日：2015-05-28

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: F16K31/126

    CPC classification number: F16K7/18 ,  F01D25/20 ,  F02K3/06 ,  F05D2260/4031 ,  F16K15/16 ,  F16N19/00

    Abstract: A fluid supply system for providing a turbomachine fluid to a component of a gas turbine engine is disclosed. The fluid supply system includes a fluid container, a moveable barrier, and an airbag. The moveable barrier fluidly divides the fluid container into a first portion and a second portion. The moveable barrier is moveable between a flow-permitting position and a flow-restricting position. The turbomachine fluid experiences a circulating flow between the component and the second portion of fluid container when the moveable barrier is in the flow-permitting position. The circulating flow is at least partially impeded by the moveable barrier when the moveable barrier is in the flow-restricting position. The airbag is positioned within the first portion of the fluid container. The airbag is selectively operable to move the moveable barrier from the flow-permitting position to the flow-restricting position.

    Abstract translation: 公开了一种用于将涡轮机流体提供给燃气涡轮发动机的部件的流体供应系统。 流体供应系统包括流体容器，可移动屏障和气囊。 可移动屏障将流体容器流体地分成第一部分和第二部分。 可移动屏障可在流动允许位置和限流位置之间移动。 当可移动屏障处于允许流动的位置时，涡轮机流体在流体容器的部件和第二部分之间经历循环流动。 当可移动屏障处于限流位置时，循环流动至少部分地被可移动屏障阻碍。 气囊位于流体容器的第一部分内。 安全气囊可选择性地可操作以将可移动屏障从流动允许位置移动到流动限制位置。

    FLUID SYSTEM WITH GRAVITY CONTROLLED VALVE
    58.
    发明申请
    FLUID SYSTEM WITH GRAVITY CONTROLLED VALVE 有权
    具有重力控制阀的流体系统

    公开(公告)号：US20140150400A1

    公开(公告)日：2014-06-05

    申请号：US13689851

    申请日：2012-11-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan Xu

    IPC: F02C7/14

    CPC classification number: F02C7/06 ,  F01M11/067 ,  F05D2260/60

    Abstract: A fluid system for use with a gas turbine engine includes a reservoir having a reservoir inlet and a reservoir outlet and includes a supply assembly positioned in the reservoir. The supply assembly includes a first passage, a second passage, and a valve disc. The first and second passages are fluidically connected to the reservoir outlet. The valve disc is positioned in the first passage. The valve disc is pivotable about an axis and is weighted to have a center of gravity offset from the axis.

    Abstract translation: 用于燃气涡轮发动机的流体系统包括具有储存器入口和储存器出口的储存器，并且包括定位在储存器中的供应组件。 供应组件包括第一通道，第二通道和阀盘。 第一和第二通道流体连接到储存器出口。 阀盘位于第一通道中。 阀盘可围绕轴线转动并且被称重以具有偏离轴的重心。

    Film Cooling Channel Array Having Anti-Vortex Properties
    59.
    发明申请
    Film Cooling Channel Array Having Anti-Vortex Properties 有权
    具有抗涡流特性的薄膜冷却通道阵列

    公开(公告)号：US20140116666A1

    公开(公告)日：2014-05-01

    申请号：US13660148

    申请日：2012-10-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan Xu

    IPC: F28F3/12

    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。

    Gas turbine engine having minimum cooling airflow
    60.
    发明授权
    Gas turbine engine having minimum cooling airflow 有权

    公开(公告)号：US11208913B2

    公开(公告)日：2021-12-28

    申请号：US16379869

    申请日：2019-04-10

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu

    IPC: F01D17/14 ,  F01D25/12 ,  F02C7/18 ,  F01D17/10 ,  F02C7/14 ,  F02C9/18 ,  B64D33/02 ,  F01D11/00 ,  F02C3/04

    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.

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