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    VARIABLE AREA FAN NOZZLE FAN FLUTTER MANAGEMENT SYSTEM
    2.
    发明申请
    VARIABLE AREA FAN NOZZLE FAN FLUTTER MANAGEMENT SYSTEM 审中-公开
    可变区风扇喷嘴风扇管理系统

    公开(公告)号：WO2013158180A3

    公开(公告)日：2013-12-12

    申请号：PCT/US2013023373

    申请日：2013-01-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GRABOWSKI ZBIGNIEW M ,  MORRIS ROBERT J ,  CARMICHAEL RAY M

    IPC: F02K1/09

    CPC classification number: F02K1/1207 ,  F01D17/06 ,  F01D25/02 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/96 ,  F05D2270/10 ,  F05D2270/304 ,  F05D2270/709

    Abstract: A gas turbine engine for an aircraft according to an exemplary aspect of the present disclosure includes, among other things, a core engine defined about an axis, a fan driven by the core engine about the axis, a core nacelle defined at least partially about the core engine, and a fan nacelle defined around the fan and at least partially around the core nacelle. Further included is a variable area fan nozzle (VAFN) to define a fan exit area downstream of the fan between the fan nacelle and the core nacelle. A controller is further included, and is operable to control a fan blade flutter characteristic.

    Abstract translation: 根据本公开的示例性方面的用于飞行器的燃气涡轮发动机尤其包括围绕轴线限定的核心发动机，由所述核心发动机绕轴线驱动的风扇，至少部分地围绕所述轴线限定的核心机舱 核心发动机和围绕风扇限定的风扇机舱，并且至少部分地围绕核心机舱。 还包括可变区域风扇喷嘴（VAFN），以在风扇机舱和核心机舱之间限定风扇下游的风扇出口区域。 还包括控制器，并且可操作以控制风扇叶片颤振特性。

    AIRFOIL PROGNOSIS FOR TURBINE ENGINES
    3.
    发明专利
    AIRFOIL PROGNOSIS FOR TURBINE ENGINES 未知

    公开(公告)号：CA2576620A1

    公开(公告)日：2007-11-16

    申请号：CA2576620

    申请日：2007-02-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TULPULE SHARAYU ,  MORRIS ROBERT J ,  LITTLES JERROL W

    IPC: F01D21/14 ,  F01D5/12 ,  F01D17/02 ,  F02C9/00 ,  G01M15/14

    Abstract: A method and control for predicting the remaining useful life of an airfoil for a gas turbine engine includes the steps of monitoring conditions of the blad e such as flutter, leaning, etc. A measured amount of deflection of the airfoil is compared to tabulated data to predict an expected crack length which is likely causing t he deflection, etc. Once a predicted crack length has been identified, the amou nt of accumulated damage to the airfoil at the crack is monitored and stored. The amount of useful life for the blade can be predicted by compiling the accumulated damage over time. The useful life remaining can be displayed such that flight plans or maintenance schedules for the aircraft can be modified as appropriate.

    HOLLOW BLADE HAVING INTERNAL DAMPER
    5.
    发明公开
    HOLLOW BLADE HAVING INTERNAL DAMPER 审中-公开
    HOHLSCHAUFEL MIT INTERNEM DEAMPFER

    公开(公告)号：EP3077625A4

    公开(公告)日：2017-01-25

    申请号：EP14867499

    申请日：2014-12-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MORRIS ROBERT J ,  BENEDICT BARRY K

    IPC: F01D5/16 ,  F01D5/18

    CPC classification number: F01D5/16 ,  F01D5/147 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2250/22 ,  F05D2250/23 ,  F05D2250/231 ,  F05D2260/96 ,  Y02T50/672

    Abstract: A hollow blade of a gas turbine engine has a sacrificial elongated damper disposed slideably in a chamber for minimizing modes of vibration during operation. The chamber is defined between two opposing surfaces generally spanning radially outward from an axis of the engine and a face facing radially inward. The damper is constructed and arranged to make loaded contact with the face via a centrifugal force created by rotation of the engine.

    Abstract translation: 燃气涡轮发动机的中空叶片具有可滑动地设置在室中的牺牲细长阻尼器，用于使操作期间的振动模式最小化。 腔室被限定在两个相对的表面之间，通常从发动机的轴线径向向外并且面向径向向内的面。 阻尼器被构造和布置成通过由发动机的旋转产生的离心力而与面部加载接触。

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