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    COOLING HOLE WITH ENHANCED FLOW ATTACHMENT
    11.
    发明申请
    COOLING HOLE WITH ENHANCED FLOW ATTACHMENT 审中-公开

    公开(公告)号：US20180038231A1

    公开(公告)日：2018-02-08

    申请号：US15237406

    申请日：2016-08-15

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu ,  Glenn Levasseur

    IPC: F01D5/18 ,  F01D9/06

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet.

    OPERABILITY GEARED TURBOFAN ENGINE INCLUDING COMPRESSOR SECTION VARIABLE GUIDE VANES
    12.
    发明申请
    OPERABILITY GEARED TURBOFAN ENGINE INCLUDING COMPRESSOR SECTION VARIABLE GUIDE VANES 审中-公开
    可操作的涡轮涡轮发动机，包括压缩机部分可变导向件

    公开(公告)号：US20150233302A1

    公开(公告)日：2015-08-20

    申请号：US14433444

    申请日：2013-10-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Glenn Levasseur ,  Gabriel L. Suciu ,  Gary M. Stetson

    IPC: F02C7/36 ,  F02C3/06 ,  F02C9/20 ,  F02C7/32

    CPC classification number: F02C7/36 ,  F01D17/162 ,  F02C3/064 ,  F02C7/32 ,  F02C9/20 ,  F05D2220/32 ,  F05D2260/4031

    Abstract: A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compressor. At least one first variable guide vane controls operation of the first compressor and at least one second variable guide vane controls operation of the second compressor. A combustor is in fluid communication with the compressor section and a turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

    Abstract translation: 燃气涡轮发动机具有风扇，该风扇包括可围绕轴线旋转的多个风扇叶片和压缩机部分，其中燃烧器部分包括第一压缩机和第一压缩机的第二压缩机。 至少一个第一可变导向叶片控制第一压缩机的操作，并且至少一个第二可变导向叶片控制第二压缩机的操作。 燃烧器与压缩机部分流体连通，并且涡轮部分与燃烧器流体连通。 齿轮架构由涡轮部分驱动，用于围绕轴线旋转风扇。

    Cooling hole with crenellation features
    14.
    发明授权
    Cooling hole with crenellation features 有权
    冷却孔具有排气功能

    公开(公告)号：US08978390B2

    公开(公告)日：2015-03-17

    申请号：US14204465

    申请日：2014-03-11

    Applicant: United Technologies Corporation

    Inventor： Glenn Levasseur ,  Edward F. Pietraszkiewicz

    IPC: F01D5/18 ,  F04D31/00 ,  F02C7/12 ,  F01D25/14

    CPC classification number: F01D25/14 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/324 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676 ,  Y10T29/49229 ,  Y10T29/49323

    Abstract: A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region.

    Abstract translation: 燃气涡轮发动机的部件的壁包括第一和第二壁表面，位于第一壁表面处的入口，位于第二表面处的出口，从入口开始并从入口的下游延伸的计量部分，以及 扩散部分从计量部分延伸并终止在出口处。 扩散部分包括形成在出口的上游端的前缘，形成在出口的下游端的后缘，在后缘的上游的身体区域，以及位于身体区域上的多个分类特征。

    COOLING ARRANGEMENT WITH CRENELLATION FEATURES FOR GAS TURBINE ENGINE COMPONENT
    16.
    发明申请
    COOLING ARRANGEMENT WITH CRENELLATION FEATURES FOR GAS TURBINE ENGINE COMPONENT 审中-公开

    公开(公告)号：US20190390567A1

    公开(公告)日：2019-12-26

    申请号：US16014467

    申请日：2018-06-21

    Applicant: United Technologies Corporation

    Inventor： JinQuan Xu ,  Glenn Levasseur

    IPC: F01D25/12 ,  F01D5/18

    Abstract: A gas turbine engine component according to an example of the present disclosure includes, among other things, a wall between first and second wall surfaces. The wall defines at least one cooling passage extending between an inlet along the first wall surface and an outlet along the second wall surface. The outlet has an upstream edge and a downstream edge with respect to a general direction of flow through the at least one cooling passage. The wall defines a plurality of crenellation features along at least the upstream edge. The upstream edge has a first profile established by the plurality of crenellation features, and the downstream edge has a second profile that differs from the first profile. A method of cooling is also disclosed.

    Multi degree of freedom flutter damper
    17.
    发明授权
    Multi degree of freedom flutter damper 有权

    公开(公告)号：US10415506B2

    公开(公告)日：2019-09-17

    申请号：US15452622

    申请日：2017-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Glenn Levasseur ,  Ryan A. Singh

    IPC: G10K11/00 ,  F02K3/06 ,  F02C7/045

    Abstract: Disclosed is a flutter damper, including an acoustic liner in fluid communication with a fluid flow, the acoustic liner being configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, and a plurality of modular chambers, each of the plurality of modular chambers being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and the plurality of modular chambers being disposed radially outside of the acoustic liner, and the plurality of modular chambers including a circumferential gap between proximate circumferential ends of at least one adjacent pair of modular chambers, wherein, the plurality of modular chambers each include a plurality of circumferentially aligned and connected chamber segments.

    ASYMMETRIC MULTI DEGREE OF FREEDOM FLUTTER DAMPER
    20.
    发明申请
    ASYMMETRIC MULTI DEGREE OF FREEDOM FLUTTER DAMPER 审中-公开

    公开(公告)号：US20180258957A1

    公开(公告)日：2018-09-13

    申请号：US15452647

    申请日：2017-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Glenn Levasseur ,  Ryan A. Singh

    IPC: F04D29/66 ,  F04D29/52 ,  F02K3/06

    CPC classification number: F02K3/06 ,  F02C7/045 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/12 ,  F05D2250/14 ,  F05D2300/121 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672

    Abstract: Disclosed is a flutter damper, including an acoustic liner in fluid communication with a fluid flow the acoustic liner being configured for peak acoustical energy absorption at a frequency range greater than a frequency range associated with fan flutter, and a plurality of modular chambers configured for peak acoustical energy absorption at a frequency range associated with one or more fan flutter modes, the plurality of modular chambers disposed radially outside the acoustic liner, the plurality of modular chambers including a circumferential gap between proximate circumferential ends of at least one adjacent pair of modular chambers, and the plurality of modular chambers each including a plurality of circumferentially aligned and connected chamber segments, and wherein at least one of the chambers in the plurality of modular chambers has a mutually unique length, width and/or height or shape.

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