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    Compressor diffuser with diffuser pipes having aero-dampers
    1.
    发明授权
    Compressor diffuser with diffuser pipes having aero-dampers 有权

    公开(公告)号：US11098650B2

    公开(公告)日：2021-08-24

    申请号：US16391627

    申请日：2019-04-23

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Krishna Prasad Balike ,  Ignatius Theratil

    IPC分类号： F02C7/24 ,  F02C3/08 ,  F04D29/66 ,  F04D29/44

    摘要： There is disclosed a diffuser pipe assembly having: a plurality of diffuser pipes circumferentially distributed around the central axis and configured for diffusing a flow of compressed air received from an impeller, the diffuser pipes having a diffuser conduit for directing the flow of compressed air, the diffuser conduit curving between an inlet end and an outlet end along a conduit axis, the diffuser conduit having a baseline surface, a first subset of the diffuser pipes having aero-dampers protruding from the baseline surfaces of their diffuser conduits such that the diffuser pipes of the first subset have a natural vibration frequency different than a natural vibration frequency of at least a second subset of the diffuser pipes.

    Airfoil with stepped spanwise thickness distribution
    4.
    发明授权
    Airfoil with stepped spanwise thickness distribution 有权

    公开(公告)号：US10718215B2

    公开(公告)日：2020-07-21

    申请号：US15808060

    申请日：2017-11-09

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Raman Warikoo ,  Krishna Prasad Balike ,  Keegan Lobo ,  Hien Duong ,  Thomas Veitch

    IPC分类号： F01D5/14 ,  F01D9/04 ,  F04D29/32

    摘要： An airfoil for a gas turbine engine comprises at least three successive sections defined between a root and a tip. A first decrease of maximum thickness-to-chord ratios defined by a difference between a maximum thickness-to-chord ratio at the root and a maximum thickness-to-chord ratio at a first spanwise position, a second decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the first spanwise position and a maximum thickness-to-chord ratio at a second spanwise position, a third decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the second spanwise position and a maximum thickness-to-chord ratio at the tip, the second decrease being greater than the corresponding first and third decreases.

    Aircraft engine with stator having varying geometry
    5.
    发明授权
    Aircraft engine with stator having varying geometry 有权

    公开(公告)号：US12091178B2

    公开(公告)日：2024-09-17

    申请号：US17804570

    申请日：2022-05-30

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Alexandre Capron ,  Karan Anand ,  Tammy Yam ,  Ali Azmi ,  Sylvain Claude ,  Krishna Prasad Balike ,  Prakul Mittal

    IPC分类号： F01D9/04 ,  B64D27/10 ,  F04D29/54

    CPC分类号： B64D27/10 ,  F01D9/041 ,  F04D29/544

    摘要： An aircraft engine, has: an upstream stator having upstream stator vanes distributed about a central axis; and a downstream stator having downstream stator vanes distributed about the central axis, the downstream stator located downstream of the upstream stator, a number of the upstream stator vanes different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes; and a second vane differing from the first vane by a geometric parameter, the geometric parameter causing the second vane to have one or more of: a stiffness greater than that of the first vane, and a major portion of a leading edge of the second vane circumferentially overlapped by another one of the upstream stator vanes.