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    AIRFOIL AND METHOD FOR IMPROVING HEAT TRANSFER OF AIRFOIL
    1.
    发明专利
    AIRFOIL AND METHOD FOR IMPROVING HEAT TRANSFER OF AIRFOIL 审中-公开

    公开(公告)号：JP2003138905A

    公开(公告)日：2003-05-14

    申请号：JP2002269736

    申请日：2002-09-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK J ,  CHON YOUNG H ,  DUBE BRYAN P

    IPC: F01D5/18 ,  F01D9/02 ,  F02C7/18

    Abstract: PROBLEM TO BE SOLVED: To provide an airfoil having an improved cooling mechanism. SOLUTION: An airfoil part of a turbine includes internal cavities 52, 54 and a plurality of indentations 90 disposed on inside surfaces 38 of the internal cavities. By the dents 90, heat transfer is improved to cool the internal cavities 52, 54 of the airfoil to elongate the service life of the airfoil, and the amount of compressor bleed air required is reduced to optimize engine efficiency. The advantage of such a cooling mechanism is that it does not restrict a cooling flow in the internal cavities 52, 54. The indentations 90 may have variable patterns or different geometric shapes.

    COOLING AN APERTURE BODY OF A COMBUSTOR WALL
    3.
    发明申请
    COOLING AN APERTURE BODY OF A COMBUSTOR WALL 审中-公开
    冷却气球墙的孔板

    公开(公告)号：WO2015147929A3

    公开(公告)日：2015-11-19

    申请号：PCT/US2014071573

    申请日：2014-12-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KOSTKA JR STANISLAV ,  CUNHA FRANK J

    IPC: F23M5/08 ,  F02C7/16 ,  F23R3/42

    CPC classification number: F23R3/005 ,  F02C7/12 ,  F23R3/06 ,  F23R2900/03042

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell, a heat shield and an annular body. The body at least partially defines a first aperture through the shell and the heat shield. The body also defines one or more second apertures through which air is directed into the first aperture and provides non-uniform cooling to the body.

    Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括燃烧器壁，其包括外壳，隔热罩和环形体。 主体至少部分地限定通过外壳和隔热罩的第一孔。 主体还限定一个或多个第二孔，空气通过该孔被引导到第一孔中并且向身体提供不均匀的冷却。

    TURBINE ENGINE MULTI-WALLED STRUCTURE WITH INTERNAL COOLING ELEMENT(S)
    4.
    发明申请
    TURBINE ENGINE MULTI-WALLED STRUCTURE WITH INTERNAL COOLING ELEMENT(S) 审中-公开
    涡轮发动机带有内部冷却元件的多壁结构（S）

    公开(公告)号：WO2015122950A3

    公开(公告)日：2015-10-22

    申请号：PCT/US2014066887

    申请日：2014-11-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK J ,  KOSTKA JR STANISLAV

    IPC: F23M5/00 ,  F02C7/12 ,  F02C7/24 ,  F23M5/08

    CPC classification number: F23R3/002 ,  F23M5/00 ,  F23M5/08 ,  F23R3/005 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/03042 ,  F23R2900/03044 ,  F23R2900/03045

    Abstract: A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.

    Abstract translation: 为涡轮发动机提供结构。 该结构包括具有第一表面的壳体和具有纹理化的第二表面和纹理化的第三表面的隔热罩。 第二表面的一部分的纹理不同于第三表面的一部分的纹理。 第一表面和第二表面限定壳体与隔热罩之间的第一冷却腔。 第一表面和第三表面限定壳体和隔热罩之间的第二冷却腔。

    VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    7.
    发明申请
    VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    VENA CONTRACTA发动机燃油涡轮增压通道

    公开(公告)号：WO2015047509A2

    公开(公告)日：2015-04-02

    申请号：PCT/US2014044873

    申请日：2014-06-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DRAKE CHRISTOPHER ,  CUNHA FRANK J ,  KOSTKA JR STANISLAV ,  JAUSE JONATHAN M ,  HANSON RUSSELL B

    IPC: F23M5/08 ,  F02C7/18 ,  F23R3/42

    CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R3/04 ,  F23R3/045 ,  F23R3/26 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括：喷嘴，其包括沿轴线的内周边。 内周边包括围绕轴的流动引导件。 用于燃气涡轮发动机的燃烧器的壁组件包括具有沿轴线的第一内周边的支撑壳体。 壁组件还包括具有沿着轴线的第二内周边的衬板，第二内周包括围绕轴的螺旋形流动引导件。 减少在燃气涡轮发动机的燃烧器衬板中的再循环进入稀释通道的方法包括对稀释通道进行轮廓化，以匹配流过其中的流体的天然收缩膜。

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