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    MISTUNED CONCENTRIC AIRFOIL ASSEMBLY AND METHOD OF MISTUNING SAME
    2.
    发明申请
    MISTUNED CONCENTRIC AIRFOIL ASSEMBLY AND METHOD OF MISTUNING SAME 审中-公开

    公开(公告)号：US20190032490A1

    公开(公告)日：2019-01-31

    申请号：US16106221

    申请日：2018-08-21

    Applicant: United Technologies Corporation

    Inventor： Richard K. Hayford ,  Steven J. Ford

    IPC: F01D5/14 ,  F01D5/02 ,  F01D25/06 ,  F01D5/22

    CPC classification number: F01D5/146 ,  F01D5/022 ,  F01D5/225 ,  F01D25/06 ,  F05D2260/961 ,  Y02T50/673

    Abstract: An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an annular shroud having a radially inner face and a radially outer face opposing the radially inner face, a radially inner array of airfoils extending from the radially inner face, and a radially outer array of airfoils extending from the radially outer face. The radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section. At least one, but fewer than each, airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and the remaining airfoils in the radially inner array of airfoils are misaligned with the airfoils of the radially outer array of airfoils. A method of reducing a vibratory response of airfoils is also disclosed.

    FLUID DAMPER AND METHOD OF MAKING
    7.
    发明申请
    FLUID DAMPER AND METHOD OF MAKING 有权
    流体阻尼器及其制造方法

    公开(公告)号：US20150361801A1

    公开(公告)日：2015-12-17

    申请号：US14698284

    申请日：2015-04-28

    Applicant: United Technologies Corporation

    Inventor： Ken F. Blaney ,  Richard K. Hayford

    IPC: F01D5/26 ,  F01D25/06 ,  F01D5/18

    CPC classification number: F01D5/26 ,  F01D5/16 ,  F01D5/18 ,  F01D25/06 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2260/96 ,  F05D2300/1606 ,  F05D2300/1614 ,  Y10T29/49341

    Abstract: An airfoil includes an airfoil structure defining a damping network that includes a first cavity, a second cavity, a flow passage connecting the first and second cavities. The airfoil further includes a damping material configured to flow through the damping network. A method of forming an airfoil includes forming an airfoil body having a damping network that includes a first cavity, a second cavity, and a flow passage connecting the first and second cavities. The method further includes adding a damping material configured to flow through the damping network.

    Abstract translation: 翼型件包括限定阻尼网络的翼型结构，该阻尼网络包括第一空腔，第二空腔，连接第一和第二空腔的流动通道。 翼型件还包括构造成流过阻尼网络的阻尼材料。 形成翼型的方法包括形成具有阻尼网络的翼型本体，所述阻尼网络包括第一空腔，第二空腔和连接第一和第二空腔的流动通道。 该方法还包括添加被配置成流过阻尼网络的阻尼材料。

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