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    FAN FOR A TURBINE ENGINE
    2.
    发明公开
    FAN FOR A TURBINE ENGINE 审中-公开

    公开(公告)号：US20240044253A1

    公开(公告)日：2024-02-08

    申请号：US17817511

    申请日：2022-08-04

    申请人： General Electric Company

    发明人： Nicholas J. Kray ,  David W. Crall ,  Anthony L. DiPietro

    IPC分类号： F01D5/14 ,  F02K3/06

    CPC分类号： F01D5/146 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/30

    摘要： A fan for a turbine engine having a core air flowpath and a bypass air flowpath. The fan includes a disk, a plurality of fan blades, and a plurality of splitter blades. The disk rotates about a centerline axis. The plurality of fan blades are coupled to the disk. The plurality of splitter blades are coupled to the disk and positioned between the plurality of fan blades. The plurality of splitter blades are axially aligned on the disk at a splitter blade axial distance from an annular inlet of the core air flowpath such that the plurality of splitter blades direct debris that passes through the fan into the bypass air flowpath.

    MISTUNED CONCENTRIC AIRFOIL ASSEMBLY AND METHOD OF MISTUNING SAME
    4.
    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

    申请人： United Technologies Corporation

    发明人： Richard K. Hayford ,  Steven J. Ford

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

    CPC分类号： F01D5/146 ,  F01D5/022 ,  F01D5/225 ,  F01D25/06 ,  F05D2260/961 ,  Y02T50/673

    摘要： 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.

    Blade with branches for an axial-flow turbomachine compressor
    7.
    发明授权
    Blade with branches for an axial-flow turbomachine compressor 有权

    公开(公告)号：US09970301B2

    公开(公告)日：2018-05-15

    申请号：US14803798

    申请日：2015-07-20

    申请人： Techspace Aero S.A.

    发明人： Stephane Hiernaux

    IPC分类号： F01D5/14 ,  F01D9/04

    CPC分类号： F01D5/146 ,  F01D9/041 ,  F04D29/544 ,  F05D2230/20 ,  F05D2230/30 ,  F05D2240/30

    摘要： A blade of a compressor or of an axial-flow turbomachine. The blade comprises a joining airfoil, or main airfoil, extended by branches, or auxiliary branch airfoils. The branches are adjacent and extend the joining airfoil radially. The branches form a row over the circumference and comprise faces facing one another. The branches comprise joining edges connected to the joining airfoil and are coincident or joined so as to form a circumferential material continuation between the adjacent branches. The leading edges and the trailing edges of the branches are a continuation of the leading edges and the trailing edges of the joining airfoil. The branch airfoils offer more anchoring points for a blade. The overlap of the branch airfoils strengthens the edges of the joining airfoil, which can thus be formed thinner. The blade comprises a fixing platform connected to the branch airfoils.