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    COMPLIANT SEAL ASSEMBLY AND METHOD OF OPERATING
    12.
    发明申请
    COMPLIANT SEAL ASSEMBLY AND METHOD OF OPERATING 审中-公开
    合适的密封组件和操作方法

    公开(公告)号：US20160177764A1

    公开(公告)日：2016-06-23

    申请号：US14938447

    申请日：2015-11-11

    Applicant: United Technologies Corporation

    Inventor： Jonathan Lemoine ,  Steven D. Porter

    IPC: F01D11/00 ,  F16J15/02

    CPC classification number: F01D11/005 ,  F01D9/065 ,  F01D11/003 ,  F01D25/162 ,  F02C7/28 ,  F05D2240/58 ,  F16J9/12 ,  F16J15/164 ,  F16J15/441 ,  F16J15/56

    Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.

    Abstract translation: 可用于燃气涡轮发动机的MTF的柔性密封组件包括围绕轴线定向的壳体，壳体中沿周向延伸的凹槽径向向外敞开。 组件的环形载体被构造和布置成在凹槽内径向移动，并且包括径向向外打开的周向延伸的通道，用于接收可密封到周围圆柱形壁的活塞环。 在操作中，托架相对于壳体径向移动以补偿壳体和壁之间的径向位移，并且活塞环沿着壁轴向移动以补偿壳体和壁之间的轴向位移。

    TURBINE VANES WITH VARIABLE FILLETS
    14.
    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
    15.
    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。

    Tapered panel rail
    16.
    发明授权
    Tapered panel rail 有权

    公开(公告)号：US11029031B2

    公开(公告)日：2021-06-08

    申请号：US16053296

    申请日：2018-08-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jon E. Sobanski ,  Steven D. Porter

    IPC: F23R3/60 ,  F23R3/00 ,  F23R3/50

    Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, and a rail disposed about a periphery of the cold side, the rail including a first rail member having a first length extending along the panel, a first height extending from the cold side, and a first thickness that varies along the first length.

    Curvic seal fitting and balance weight locations
    18.
    发明授权
    Curvic seal fitting and balance weight locations 有权

    公开(公告)号：US10738639B2

    公开(公告)日：2020-08-11

    申请号：US15156993

    申请日：2016-05-17

    Applicant: United Technologies Corporation

    Inventor： Steven D. Porter ,  Thomas A. Mariano

    IPC: F01D11/00 ,  F01D25/04 ,  F01D5/02

    Abstract: Aspects of the disclosure are directed to a seal comprising: a first fitting configured to couple to a first disk, and a curvic joint including curvic teeth, where a first distance between the first fitting and the curvic teeth is equal to or greater than a first thickness of the first disk. In some embodiments, an engine comprises: a compressor disk, a turbine disk, and a seal including: a first fitting configured to couple to the turbine disk, a second fitting configured to couple to the compressor disk, and a curvic joint including curvic teeth, where a first axial distance between the first fitting and the curvic teeth is greater than or equal to a first radial thickness of the turbine disk.

    Swirler for combustor of gas turbine engine
    19.
    发明授权
    Swirler for combustor of gas turbine engine 有权

    公开(公告)号：US10591163B2

    公开(公告)日：2020-03-17

    申请号：US15656742

    申请日：2017-07-21

    Applicant: United Technologies Corporation

    Inventor： Steven D. Porter ,  Cara M. Redding

    IPC: F23R3/14 ,  F23R3/28 ,  F23C7/00

    Abstract: A combustor for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber, and a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion. The fuel injector includes a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis. A swirler for a gas turbine engine includes a swirler entrance and a swirler exit. The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.

    ELECTROSTATIC FLAME CONTROL TECHNOLOGY
    20.
    发明申请
    ELECTROSTATIC FLAME CONTROL TECHNOLOGY 审中-公开

    公开(公告)号：US20200003165A1

    公开(公告)日：2020-01-02

    申请号：US16020021

    申请日：2018-06-27

    Applicant: United Technologies Corporation

    Inventor： Steven D. Porter ,  Jon E. Sobanski

    IPC: F02M27/04 ,  F02B23/10 ,  F02M39/00 ,  F23C99/00 ,  F23D11/24 ,  F23D11/32

    Abstract: A method of controlling fuel injection into a combustor of a gas turbine engine including: applying a first electrical charge to fuel such that the fuel becomes a charged fuel; and applying a second electrical charge to a component of the combustor, wherein the first electrical charge is applied to the fuel at a first frequency and the second electrical charge is applied to the component at a second frequency such that at least one of a selected tone, a selected screech, and a selected noise is produced by spraying the charged fuel through the component and into a combustion chamber of the combustor from a fuel nozzle.

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