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    TURBINE VANE WITH VARIABLE TRAILING EDGE INNER RADIUS
    11.
    发明申请
    TURBINE VANE WITH VARIABLE TRAILING EDGE INNER RADIUS 审中-公开
    涡轮风扇与可变轨迹边缘内径半径

    公开(公告)号：US20160069197A1

    公开(公告)日：2016-03-10

    申请号：US14787490

    申请日：2014-05-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Steven D. Porter ,  John T. Ols

    IPC: F01D9/02

    CPC classification number: F01D9/023 ,  F01D5/141 ,  F01D5/18 ,  F01D9/047 ,  F01D25/162 ,  F05D2240/122 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine vane has an airfoil extending between an inner platform and an outer platform. The airfoil is hollow. A hollow within the airfoil extends between an inner leading edge to an inner trailing edge. An inner radius is defined at the inner trailing edge in a circumferential direction measured between walls which extend from the inner leading edge to the inner trailing edge. The inner radius varies along a radial length defined between the inner and outer platforms. A mid-turbine frame and a gas turbine engine are also disclosed.

    Abstract translation: 涡轮叶片具有在内平台和外平台之间延伸的翼型件。 翼型是空心的。 翼型内的中空部分在内前缘到内后缘之间延伸。 在从内部前缘延伸到内部后缘的壁之间测量的在圆周方向上的内部后缘处限定内部半径。 内半径沿着内平台和外平台之间限定的径向长度而变化。 还公开了中涡轮机架和燃气涡轮发动机。

    GAS TURBINE ENGINE MID-TURBINE FRAME CONFIGURATION
    14.
    发明申请
    GAS TURBINE ENGINE MID-TURBINE FRAME CONFIGURATION 有权
    气体涡轮发动机中间涡轮机框架配置

    公开(公告)号：US20160245105A1

    公开(公告)日：2016-08-25

    申请号：US14629090

    申请日：2015-02-23

    Applicant: United Technologies Corporation

    Inventor： Jorge I. Farah ,  John T. Ols

    IPC: F01D9/04 ,  F01D25/24 ,  F01D11/00

    CPC classification number: F01D9/041 ,  F01D9/042 ,  F01D9/065 ,  F01D11/005 ,  F01D25/162 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F05D2220/3213 ,  F05D2230/21 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/31

    Abstract: A gas turbine engine includes a core flow path that extends axially about an engine axis. A turbine section is arranged in the core flow path. A mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of the core flow path. The vanes and inner and outer flow path surfaces are provided by a unitary, one-piece cast structure. The inner flow path surface provides inlet and exit inner diameters relative to the engine axis. The outer flow path surface provides inlet and exit outer diameters relative to the engine axis. The inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter. A ratio of the exit outer diameter to the axial length is greater than 3.0 to 1.

    Abstract translation: 燃气涡轮发动机包括围绕发动机轴线轴向延伸的铁心流路。 涡轮部分布置在核心流动路径中。 中间涡轮机框架包括多个周向间隔开的叶片，其在限定芯流动路径的一部分之间径向延伸并且互连内部和外部流动路径表面。 叶片和内部和外部流动路径表面由单一的一体式铸造结构提供。 内部流路表面相对于发动机轴线提供入口和出口内径。 外部流路表面相对于发动机轴线提供入口和出口外径。 内部流路表面从入口内径延伸到出口内径的轴向长度。 出口外径与轴向长度之比大于3.0比1。

    TURBINE VANES WITH VARIABLE FILLETS
    16.
    发明申请
    TURBINE VANES WITH VARIABLE FILLETS 审中-公开
    具有可变填料的涡轮风扇

    公开(公告)号：US20160123166A1

    公开(公告)日：2016-05-05

    申请号：US14890496

    申请日：2014-06-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： John T. Ols ,  Karl A. Mentz ,  Richard N. Allen ,  Steven D. Porter ,  Renee J. Jurek ,  Paul K. Sanchez ,  Sandra S. Pinero

    IPC: F01D9/04 ,  F01D25/24 ,  F01D5/02

    CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/143 ,  F01D9/04 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/80 ,  F05D2250/71 ,  F05D2250/90 ,  Y02T50/673

    Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

    Abstract translation: 翼型件在径向内部和径向外部平台之间延伸。 翼型件在前缘和后缘之间延伸，并且合并到径向内外平台的相对表面中。 可变圆角将径向内平台和外平台之一的相对表面合并成翼型的壁。 可变圆角具有远离翼型件的表面延伸的长度以及远离径向内部和外部平台中的至少一个的相对表面向外延伸到翼型的高度。 可变圆角在前缘和后缘之一处具有更大的长度。 间隔部分在与前缘和后缘中的至少一个间隔开的位置处具有较短的长度。 还公开了中涡轮机架和燃气涡轮发动机。

    Turbine Vane With Non-Uniform Wall Thickness
    18.
    发明申请
    Turbine Vane With Non-Uniform Wall Thickness 审中-公开
    涡轮叶片具有不均匀的壁厚

    公开(公告)号：US20160061046A1

    公开(公告)日：2016-03-03

    申请号：US14787349

    申请日：2014-05-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： John T. Ols ,  Richard N. Allen ,  Steven D. Porter

    IPC: F01D9/04 ,  F01D5/14

    CPC classification number: F01D9/041 ,  F01D5/143 ,  F01D9/042 ,  F01D9/047 ,  F01D25/24 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/80 ,  Y02T50/673

    Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.

    Abstract translation: 用于燃气涡轮发动机的叶片具有在前缘和后缘之间延伸的翼型件，并且通常是中空的。 叶片具有径向外部平台和径向内部平台。 径向内部和径向外部平台中的至少一个具有沿着前缘和后缘之一周向定位的较厚部分，并且较薄的部分周向地超过翼型的圆周边缘。 还公开了中涡轮机架和燃气涡轮发动机。

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