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    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。

    GAS TURBINE HUB
    6.
    发明申请
    GAS TURBINE HUB 审中-公开

    公开(公告)号：WO2015020715A3

    公开(公告)日：2015-02-12

    申请号：PCT/US2014/039091

    申请日：2014-05-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： BURD, Steven W. ,  HARRIS, Meggan ,  OLS, John T. ,  ASKEY, William G.

    IPC: F01D5/02 ,  F01D5/30

    Abstract: A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.

    TURBINE VANE WITH PLATFORM PAD
    7.
    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。

    INTERRUPTED MIDRAIL FOR COMBUSTOR PANEL
    9.
    发明公开
    INTERRUPTED MIDRAIL FOR COMBUSTOR PANEL 审中-公开

    公开(公告)号：EP3587926A1

    公开(公告)日：2020-01-01

    申请号：EP19182920.9

    申请日：2019-06-27

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  OLS, John T. ,  ICHIHASHI, Fumitaka

    IPC: F23R3/00 ,  F23R3/06 ,  F23R3/26 ,  F23R3/50

    Abstract: A heat shield panel (800) for a gas turbine engine combustor (24) may comprise a perimetrical rail (850) extending at least partially around a perimeter of the heat shield panel (800) and defining a main backside cavity (860), a plurality of air admittance holes (778), each air admittance hole (778) extending along a hole axis, and a midrail (858) dividing the main backside cavity (860) into a first backside cavity (861) and a second backside cavity (862), wherein at least a portion of the midrail (858) is axially offset from at least one of the hole axes.

    TURBINE VANE WITH PLATFORM PAD
    10.
    发明公开
    TURBINE VANE WITH PLATFORM PAD 审中-公开
    涡轮叶片与平台垫

    公开(公告)号：EP3011141A1

    公开(公告)日：2016-04-27

    申请号：EP14813485.1

    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

    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: 叶片具有在径向外部平台和径向内部平台之间延伸的翼型。 至少一个平台具有名义上径向较薄的部分，以及限定径向较厚部分的垫。 垫的径向厚度大于标称的径向较薄部分的厚度。 垫在径向外平台的一侧围绕翼型的外周。 垫具有不同的径向厚度。 还公开了中间涡轮机框架和燃气涡轮发动机。

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