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    TURBINE VANE WITH PLATFORM PAD
    2.
    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
    3.
    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。

    TURBINE VANE WITH PLATFORM PAD
    5.
    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。

    AIRFOIL
    7.
    发明公开
    AIRFOIL 审中-公开
    翼型

    公开(公告)号：EP3219919A1

    公开(公告)日：2017-09-20

    申请号：EP17160960.5

    申请日：2017-03-14

    Applicant: United Technologies Corporation

    Inventor： LEON, Jeffrey ,  NADEAU, Daniel C. ,  LEVINE, Jeffrey R. ,  KAUFMAN, Eleanor D. ,  ALLEN, Richard N. ,  MOLONY, Evan P. ,  ANSELMI, Gregory

    IPC: F01D5/18 ,  B22C9/10

    Abstract: An airfoil (200), comprising an airfoil body and an internal cavity (210) within the airfoil body. The internal cavity (210) may comprise an outer edge (212) comprising a first outer scallop (213) and a second outer scallop (213), an inner edge (211) opposite the outer edge (212), the inner edge (211) comprising a first inner scallop (213) and a second inner scallop (213), a leading edge (208) spanning between the outer edge (212) and the inner edge (211), and a trailing edge (209) spanning between the outer edge (212) and the inner edge (211) and opposite the leading edge (208). Between the outer edge (212), the inner edge (211), the leading edge (208), and the trailing edge (209), the internal cavity may comprise eight columns of pedestals (221...228) disposed axially relative to one another and axially between the leading edge (208) and the trailing edge (209).

    Abstract translation: 一种翼型（200），包括翼型主体和翼型主体内的内腔（210）。 内腔210可以包括外边缘212，该外边缘212包括第一外扇贝213和第二外扇贝213，与外边缘212相对的内边缘211， ）包括第一内扇贝（213）和第二内扇贝（213），跨越外边缘（212）和内边缘（211）之间的前缘（208），以及跨越 外边缘（212）和内边缘（211）并与前缘（208）相对。 在外边缘（212），内边缘（211），前缘（208）和后缘（209）之间，内腔可以包括相对于轴向设置的八列基座（221 ... 228） 彼此并且在前缘（208）和后缘（209）之间轴向地延伸。

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