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    TURBINE VANE WITH PLATFORM PAD
    3.
    发明申请
    TURBINE VANE WITH PLATFORM PAD 审中-公开
    涡轮风扇平台

    公开(公告)号：WO2014204608A1

    公开(公告)日：2014-12-24

    申请号：PCT/US2014/038914

    申请日：2014-05-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： OLS, John T. ,  ALLEN, Richard N. ,  PORTER, Steven D. ,  SANCHEZ, Paul K. ,  PINERO, Sandra S.

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

    CPC classification number: F01D9/042 ,  F01D5/14 ,  F01D5/141 ,  F01D9/02 ,  F01D9/04 ,  F01D9/047 ,  F01D25/24 ,  F05D2230/53 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

    Abstract translation: 叶片具有在径向外平台和径向内平台之间延伸的翼型件。 至少一个平台具有标称径向较薄的部分，以及限定径向较厚部分的垫。 垫的径向厚度大于标称径向较薄部分的厚度。 垫片围绕在径向外平台的一侧的翼型件的外周边。 垫具有变化的径向厚度。 还公开了中涡轮机架和燃气涡轮发动机。

    TURBINE VANES WITH VARIABLE FILLETS
    4.
    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：WO2015009418A1

    公开(公告)日：2015-01-22

    申请号：PCT/US2014/044039

    申请日：2014-06-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： OLS, John T. ,  MENTZ, Karl A. ,  ALLEN, Richard N. ,  PORTER, Steven D. ,  JUREK, Renee J. ,  SANCHEZ, Paul K. ,  PINERO, Sandra S.

    IPC: F01D9/04 ,  F01D5/14 ,  F02C7/04

    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。

    ELECTROSTATIC FLAME CONTROL TECHNOLOGY
    9.
    发明公开
    ELECTROSTATIC FLAME CONTROL TECHNOLOGY 审中-公开

    公开(公告)号：EP3587921A3

    公开(公告)日：2020-02-12

    申请号：EP19183017.3

    申请日：2019-06-27

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  SOBANSKI, Jon E.

    IPC: F23D11/32 ,  F02C7/22 ,  F23C99/00 ,  F23R3/28

    Abstract: A method (600) of controlling fuel injection into a combustor (56) of a gas turbine engine (20) including: applying a first electrical charge (212) to fuel (72) such that the fuel becomes a charged fuel (720); and applying a second electrical charge (214) to a component (250) 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 (54) of the combustor from a fuel nozzle (78).

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