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    TURBINE VANES WITH VARIABLE FILLETS
    2.
    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。

    MID-TURBINE DUCT FOR GEARED GAS TURBINE ENGINE
    4.
    发明申请
    MID-TURBINE DUCT FOR GEARED GAS TURBINE ENGINE 审中-公开
    用于齿轮式涡轮发动机的中涡轮泵

    公开(公告)号：US20150240712A1

    公开(公告)日：2015-08-27

    申请号：US14608304

    申请日：2015-01-29

    Applicant: United Technologies Corporation

    Inventor： Renee J. Jurek ,  Thomas J. Praisner

    IPC: F02C3/06 ,  F01D9/04 ,  F02C7/057

    CPC classification number: F01D5/143 ,  F01D9/041 ,  F05D2220/3213 ,  Y02T50/673

    Abstract: A mid-turbine vaned duct comprises a duct upstream end to abut a downstream end of an upstream turbine rotor. A duct downstream end abuts an upstream end of a downstream turbine rotor. The vaned duct includes a first gap extending between the upstream turbine rotor and an upstream end of a vane positioned within the duct, intermediate the vaned duct upstream and downstream ends. A second gap is defined between a downstream end of the vane and the downstream turbine rotor. The first gap extends for a first axial distance and the second gap extends for a second axial distance. A length ratio of the first axial distance to the second axial distance is less than or equal to 2.0.

    Abstract translation: 中涡轮叶片管道包括用于邻接上游涡轮转子的下游端的管道上游端。 管道下游端邻接下游涡轮转子的上游端。 所述带式管道包括在所述上游涡轮机转子和位于所述管道内的叶片的上游端之间延伸的第一间隙，所述第一间隙位于所述带通管道上游和下游端部的中间。 第二间隙限定在叶片的下游端和下游涡轮转子之间。 第一间隙延伸第一轴向距离，第二间隙延伸第二轴向距离。 第一轴向距离与第二轴向距离的长度比小于或等于2.0。

    CONTOURED FLOWPATH SURFACE
    5.
    发明申请
    CONTOURED FLOWPATH SURFACE 审中-公开
    轮廓流动面

    公开(公告)号：US20150204201A1

    公开(公告)日：2015-07-23

    申请号：US14421645

    申请日：2013-03-15

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Turner ,  Andrew G. Alarcon ,  James Glaspey ,  Brian Green ,  Barry M. Ford ,  Renee J. Jurek

    IPC: F01D5/30 ,  F01D5/02

    CPC classification number: F01D5/30 ,  F01D5/02 ,  F01D5/143 ,  F01D5/145 ,  F01D11/008 ,  F05D2220/32 ,  F05D2240/55 ,  Y02T50/673

    Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.

    Abstract translation: 用于燃气涡轮发动机的转子组件的间隔件组件包括具有非轴对称流路表面的端壁段，第一凹陷和第二凹陷。 流路表面的周边包括前边缘，后边缘，吸力侧边缘和压力侧边缘。 第一凹部沿着与吸力侧边缘相邻的流路面形成，第二凹部沿着与压力侧边缘相邻的流路面形成。

    Endwall Controuring
    9.
    发明申请
    Endwall Controuring 有权
    端壁控制

    公开(公告)号：US20140090401A1

    公开(公告)日：2014-04-03

    申请号：US13663977

    申请日：2012-10-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Thomas J. Praisner ,  Andrew S. Aggarwala ,  Eric A. Grover ,  Renee J. Jurek

    IPC: F01D9/00 ,  F02C3/04

    CPC classification number: F01D5/145 ,  F01D5/143 ,  F04D29/324 ,  F04D29/329 ,  F04D29/547 ,  F04D29/681 ,  F05D2240/123 ,  F05D2240/305 ,  F05D2250/712 ,  Y02T50/673

    Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.

    Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型阵列还可以包括从邻近所述多个翼型中的至少一个翼型件的第一侧的端壁延伸并且在所述多个翼型中的至少一个翼型件的前缘附近的凸形轮廓区域。 所述翼型阵列还可包括邻近所述多个翼型件中的所述至少一个翼型件的第一侧和所述凸形轮廓区域的后部的所述端壁中的凹形轮廓区域。

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