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    FAN EXIT GUIDE VANE PLATFORM CONTOURING
    1.
    发明申请
    FAN EXIT GUIDE VANE PLATFORM CONTOURING 审中-公开
    风扇退出指南VANE PLATFORM CONTOURING

    公开(公告)号：US20160017715A1

    公开(公告)日：2016-01-21

    申请号：US14774190

    申请日：2014-03-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Flavien L. Thomas

    IPC: F01D5/14 ,  F01D9/02 ,  F02K3/06

    CPC classification number: F01D5/143 ,  F01D9/023 ,  F02K3/06 ,  F05D2220/36 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

    Abstract: A turbofan engine includes a fan section with a plurality of fan blades rotatable about an engine axis generating an airflow, a bypass passage through which the airflow passes, and a fan exit guide vane. The fan exit guide vane assembly includes a plurality of airfoils disposed between an inner platform wall and an outer platform wall. At least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent airfoils. The contoured surface includes at least one concave region and at least one convex region. A method of reducing secondary flow structures in bypass air flow with the turbofan is also disclosed.

    Abstract translation: 涡轮风扇发动机包括：风扇部分，其具有围绕产生气流的发动机轴线可旋转的多个风扇叶片，气流通过的旁通通道和风扇出口导叶。 风扇出口导叶组件包括设置在内平台壁和外平台壁之间的多个翼型件。 内平台壁和外平台壁中的至少一个包括相邻翼型之间的轮廓表面。 轮廓表面包括至少一个凹区域和至少一个凸区域。 还公开了一种减少涡轮风扇旁路气流二次流结构的方法。

    Fan exit guide vane platform contouring
    2.
    发明授权
    Fan exit guide vane platform contouring 有权

    公开(公告)号：US10196897B2

    公开(公告)日：2019-02-05

    申请号：US14774190

    申请日：2014-03-13

    Applicant: United Technologies Corporation

    Inventor： Flavien L. Thomas

    IPC: F01D5/14 ,  F02K3/06 ,  F01D9/02

    Abstract: A turbofan engine includes a fan section with a plurality of fan blades rotatable about an engine axis generating an airflow, a bypass passage through which the airflow passes, and a fan exit guide vane. The fan exit guide vane assembly includes a plurality of airfoils disposed between an inner platform wall and an outer platform wall. At least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent airfoils. The contoured surface includes at least one concave region and at least one convex region. A method of reducing secondary flow structures in bypass air flow with the turbofan is also disclosed.

    Endwall contouring for airfoil rows with varying airfoil geometries
    3.
    发明授权
    Endwall contouring for airfoil rows with varying airfoil geometries 有权

    公开(公告)号：US10151210B2

    公开(公告)日：2018-12-11

    申请号：US14816113

    申请日：2015-08-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Flavien L. Thomas

    IPC: F01D11/00 ,  F01D5/02 ,  F01D5/14 ,  F01D9/04 ,  F04D29/54 ,  F04D29/32

    Abstract: An airfoil array for a gas turbine engine comprises a plurality of airfoils spaced circumferentially apart from each other about an engine center axis. Each airfoil is associated with a platform. An endwall extends circumferentially about the engine center axis, and is defined by adjacent platforms. Each pair of adjacent platforms are separated from each other by a gap. An endwall contour shape extends from a first location on one side of the gap to a second location on an opposite of the gap. The endwall contour shape is the same for all adjacent platforms. A gas turbine engine and a method of forming an airfoil array for a gas turbine engine are also disclosed.

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