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    INLET GUIDE VANE HAVING A VARIED TRAILING EDGE GEOMETRY
    1.
    发明申请
    INLET GUIDE VANE HAVING A VARIED TRAILING EDGE GEOMETRY 审中-公开

    公开(公告)号：US20190078450A1

    公开(公告)日：2019-03-14

    申请号：US15698997

    申请日：2017-09-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James A. Eley ,  Eric A. Grover ,  Thomas J. Praisner

    IPC: F01D9/04 ,  F01D5/14 ,  F01D17/16

    Abstract: An inlet guide vane having varied trailing edge geometry is provided. The inlet guide vane may have an inner diameter edge opposite an outer diameter edge, and may comprise a leading edge part and a trailing edge part. The trailing edge part may comprise a trailing edge length defining a length between a forward edge and an aft edge. The trailing edge length may vary in length. The trailing edge part may be displaced from the leading edge part at a stagger angle. The stagger angle may vary in displacement.

    SYSTEMS AND METHODS FOR VANE COOLING
    5.
    发明申请
    SYSTEMS AND METHODS FOR VANE COOLING 审中-公开
    用于风扇冷却的系统和方法

    公开(公告)号：US20160237850A1

    公开(公告)日：2016-08-18

    申请号：US14623473

    申请日：2015-02-16

    Applicant: United Technologies Corporation

    Inventor： Pitchaiah V. Chakka ,  Carey Clum ,  Thomas J. Praisner ,  Jesse R. Christophel

    IPC: F01D25/12 ,  B23H1/00 ,  F01D9/04

    CPC classification number: F01D25/12 ,  B23H1/00 ,  F01D5/186 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/12 ,  F05D2240/12 ,  F05D2250/314 ,  F05D2260/202 ,  Y02T50/676

    Abstract: An airfoil is disclosed comprising a distal edge, a proximal edge, a pressure side surface extending between the distal edge and the proximal edge and between a leading edge and a trailing edge, the leading edge forward of the trailing edge, wherein a first cooling hole and a second cooling hole are disposed in the pressure side surface, wherein the first cooling hole is oriented at a first angle relative to the distal edge and the second cooling hole is oriented at a second angle relative to the proximal edge, wherein the first angle and the second angle have bilateral symmetry about a plane, wherein the plane is located at a point at least one of more than or less than the midpoint between the distal edge and proximal edge.

    Abstract translation: 公开了一种翼型件，其包括远侧边缘，近侧边缘，在远侧边缘和近侧边缘之间以及前缘和后缘之间以及后缘前方的前缘延伸的压力侧表面，其中第一冷却孔 并且第二冷却孔设置在所述压力侧表面中，其中所述第一冷却孔相对于所述远侧边缘以第一角度定向，并且所述第二冷却孔相对于所述近侧边缘以第二角度定向，其中所述第一角度 并且所述第二角度具有关于平面的双边对称性，其中所述平面位于所述远侧边缘和近侧边缘之间的中点之中至少一个以上的点处。

    Endwall contouring
    6.
    发明授权
    Endwall contouring 有权
    端壁轮廓

    公开(公告)号：US09212558B2

    公开(公告)日：2015-12-15

    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 ,  F01D5/14

    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。

    Gas turbine engine mid turbine frame with flow turning features
    7.
    发明授权
    Gas turbine engine mid turbine frame with flow turning features 有权
    燃气涡轮发动机中涡轮机架具有流动转向特征

    公开(公告)号：US08561414B1

    公开(公告)日：2013-10-22

    申请号：US13778202

    申请日：2013-02-27

    Applicant: United Technologies Corporation

    Inventor： Thomas J. Praisner ,  Shankar S. Magge ,  Matthew B. Estes

    IPC: F02D9/02

    CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D9/04 ,  F01D9/065 ,  F01D25/28 ,  F02K3/06 ,  F05D2240/12 ,  Y02T50/673

    Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.

    Abstract translation: 燃气涡轮发动机包括具有旋转轴线的第一和第二级。 在第一阶段和第二阶段之间轴向布置有圆周阵列的翼型件。 至少一个翼型件具有在压力侧和吸力侧之间等距离设置的曲率。 翼型件从翼缘沿着翼型在中跨平面处从前缘延伸到后缘。 第一和第二线之间的角度分别与翼型前缘和后缘的中跨平面和曲率的交点相切。 该角度等于或大于约10°。

    CASE FOR GAS TURBINE ENGINE
    8.
    发明申请
    CASE FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20190292915A1

    公开(公告)日：2019-09-26

    申请号：US15928133

    申请日：2018-03-22

    Applicant: United Technologies Corporation

    Inventor： Jonathan Jeffery Eastwood ,  Curtis L. Memory ,  Jin Hu ,  Thomas J. Praisner

    IPC: F01D5/14 ,  F01D25/24 ,  F01D9/04 ,  F15D1/00

    Abstract: A strut for a gas turbine engine includes an airfoil section extending in a spanwise direction between a first platform and a second platform, extending in a chordwise direction between a leading edge and trailing edge to define a chord length, and extending in a thickness direction between a first side and a second side to define a chord width. Exterior surfaces of the airfoil section define a leading portion between the leading edge and a widest location of the airfoil section relative to the thickness direction, and a trailing portion between the widest location and the trailing edge. The exterior surfaces establish a respective exterior contour for each span position between a 0% span position and a 100% span position. The exterior surfaces define a plurality of dimples in the leading portion.

    MID-TURBINE DUCT FOR GEARED GAS TURBINE ENGINE
    10.
    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。

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