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27 条记录 (耗时 0.013 秒)

    FLUID MACHINE FOR AN AIRCRAFT ENGINE AND AIRCRAFT ENGINE
    1.
    发明公开
    FLUID MACHINE FOR AN AIRCRAFT ENGINE AND AIRCRAFT ENGINE 审中-公开

    公开(公告)号：EP4144960A1

    公开(公告)日：2023-03-08

    申请号：EP22193989.5

    申请日：2022-09-05

    申请人： Pratt & Whitney Canada Corp.

    发明人： DUONG, Hien ,  KANDASAMY, Vijay

    IPC分类号： F01D5/14 ,  F01D9/04

    摘要： A fluid machine for an aircraft engine has first and second walls, a gaspath defined between the first wall and the second wall; a rotor having blades rotatable about the central axis (11) and a stator (24) having a row of vanes having airfoils including leading edges (35A), trailing edges (35B), pressure sides (35C) and suction sides (35D) opposed the pressure sides (35C), and depressions (40) defined in the first wall, the depressions (40) extending from a baseline surface of the first wall away from the second wall, a depression (40) of the depressions (40) located circumferentially between a pressure side (35C) of the pressure sides (35C) and a suction side (35D) of the suction sides (35D), the depression (40) axially overlapping the airfoils and located closer to the suction side (35D) than to the pressure side (35C), an upstream end of the depression (40) located closer to a leading edge (35A) of the leading edges (35A) than to a trailing edge (35B) of the trailing edges (35B).

    COMPRESSOR DIFFUSER AND DIFFUSER PIPES THEREFOR
    2.
    发明公开
    COMPRESSOR DIFFUSER AND DIFFUSER PIPES THEREFOR 审中-公开

    公开(公告)号：EP4015833A1

    公开(公告)日：2022-06-22

    申请号：EP21215296.1

    申请日：2021-12-16

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： DUONG, Hien ,  NICHOLS, Jason

    IPC分类号： F04D17/10 ,  F04D29/44 ,  F04D29/68

    摘要： A diffuser for a compressor of a gas turbine engine is disclosed. The diffuser has a plurality of diffuser pipes (40) circumferentially distributed about an axis of the compressor, each of the plurality of diffuser pipes (40) extending from an inlet to an outlet and having a bend section (45) between the inlet and the outlet, a low pressure side and an opposite high pressure side. A recirculation conduit (50) defines a recirculation path from a first flow region to a second flow region in one or more of the plurality of the diffuser pipes (40), the first flow region having a greater static pressure than that of the second region, the recirculation conduit (50) having a conduit inlet (51) and a conduit outlet (52), at least the conduit outlet (52) located within the low pressure side of one of the plurality of the diffuser pipes (40).

    INTER-COMPRESSOR FLOW DIVIDER PROFILING
    3.
    发明公开
    INTER-COMPRESSOR FLOW DIVIDER PROFILING 审中-公开

    公开(公告)号：EP3660272A1

    公开(公告)日：2020-06-03

    申请号：EP19211952.7

    申请日：2019-11-27

    申请人： Pratt & Whitney Canada Corp.

    发明人： NICHOLS, Jason ,  TOWNSEND, Peter ,  VEITCH, Thomas ,  DUONG, Hien ,  WATSON, Guilherme

    IPC分类号： F01D9/06 ,  F01D9/04 ,  F01D25/24 ,  F01D25/16 ,  F04D29/44 ,  F04D29/40

    摘要： An inter-compressor case (5) for a gas turbine engine comprises: an outer casing (11) and an inner casing radially spaced apart relative to a longitudinal axis (20); a gas path extending from a plurality of radial inlets (13) arranged in a circumferentially spaced apart array around the outer casing (11) to an annular outlet (14) defined by an axially extending downstream portion of the outer casing (11) and an axially extending downstream portion of the inner casing; a plurality of struts having a gas path surface extending across the gas path between the outer casing (11) and the inner casing; and a plurality of flow separators extending from the adjacent radial inlets (13). The flow separators have trailing edges disposed upstream of the annular outlet (14) and include a plurality of full length flow separators and a plurality of truncated flow separators.

    FLUID MACHINE FOR AN AIRCRAFT ENGINE AND AIRCRAFT ENGINE
    6.
    发明公开
    FLUID MACHINE FOR AN AIRCRAFT ENGINE AND AIRCRAFT ENGINE 审中-公开

    公开(公告)号：EP4144959A1

    公开(公告)日：2023-03-08

    申请号：EP22193983.8

    申请日：2022-09-05

    申请人： Pratt & Whitney Canada Corp.

    发明人： DUONG, Hien ,  KANDASAMY, Vijay

    IPC分类号： F01D5/14 ,  F01D9/04

    摘要： A fluid machine has first (21A) and second walls (21B), a gaspath defined between the first wall (21A) and the second wall (21B); a rotor having blades rotatable about the central axis (11) and a stator (31) having a row of vanes (33) having airfoils (35) including leading edges (35A), trailing edges (35B), pressure sides (35C) and suction sides (35D) opposed the pressure sides (35C), and depressions (40) defined in the first wall (21A), the depressions (40) extending from a baseline surface (BS) of the first wall (21A) away from the second wall (21B), a depression (40) of the depressions (40) located circumferentially between a pressure side (35C) of the pressure sides (35C) and a suction side (35D) of the suction sides (35D), the depression (40) axially overlapping the airfoils (35) and extending in a downstream direction from an upstream end to a downstream end, the downstream end located closer to a trailing edge (35B) of the trailing edges (35B) than to a leading edge (35A) of the leading edges (35A).

    IMPELLER EXDUCER CAVITY WITH FLOW RECIRCULATION
    7.
    发明公开
    IMPELLER EXDUCER CAVITY WITH FLOW RECIRCULATION 审中-公开

    公开(公告)号：EP3964716A1

    公开(公告)日：2022-03-09

    申请号：EP21195617.2

    申请日：2021-09-08

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： DUONG, Hien

    IPC分类号： F04D29/28 ,  F04D29/68

    摘要： A centrifugal compressor (140) for an aircraft engine is disclosed, having an impeller (150) mounted for rotation about an axis (11). The impeller (150) has impeller blades (151) extending from an inducer end (153) to an exducer end (154). A shroud (160) extends over the impeller blades (151). A main flow passage (FP) is defined between the shroud (160) and the impeller (150), a cavity (180) fluidly communicates with the main flow passage (FP) via at least one extraction port (181) and at least one reinjection port (182). The reinjection port (182) is fluidly connected to the main flow passage (FP) upstream of the extraction port (181) relative to a flow direction through the main flow passage (FP). The reinjection port (182) is disposed upstream of the exducer end (154) of the impeller blade, in an exducer portion (EX) of the shroud (160).

    DIFFUSER PIPE WITH RADIALLY-OUTWARD EXIT
    8.
    发明公开
    DIFFUSER PIPE WITH RADIALLY-OUTWARD EXIT 审中-公开

    公开(公告)号：EP3832144A1

    公开(公告)日：2021-06-09

    申请号：EP20212299.0

    申请日：2020-12-07

    申请人： Pratt & Whitney Canada Corp.

    发明人： KISUN, Gavin ,  YU, Hong ,  DUONG, Hien

    IPC分类号： F04D29/44 ,  F02C3/08

    摘要： A diffuser pipe (20) has a tubular body (22) with a first portion (24) extending from an inlet (23) of the diffuser pipe (20), a second portion (26) extending along a generally axial direction relative to a center axis (11), and a bend portion (28) fluidly connecting the first and second portions (24, 26). An exit segment (27) of the second portion (26) defines a pipe outlet (25). The exit segment (27) is curved radially outwardly relative to the center axis (11).

    COMPRESSOR AIRFOIL AND METHOD OF FORMING A BLADE
    9.
    发明公开
    COMPRESSOR AIRFOIL AND METHOD OF FORMING A BLADE 审中-公开
    VERDICHTERSCHAUFEL UND VERFAHREN ZUR HERSTELLUNG EINER SCHAUFEL

    公开(公告)号：EP2990602A1

    公开(公告)日：2016-03-02

    申请号：EP15182514.8

    申请日：2015-08-26

    申请人： Pratt & Whitney Canada Corp.

    发明人： NICHOLS, Jason ,  DUONG, Hien

    IPC分类号： F01D5/14 ,  F04D29/32

    CPC分类号： F04D29/384 ,  F01D5/141 ,  F01D5/145 ,  F04D19/00 ,  F04D19/02 ,  F04D29/324 ,  F05D2240/303 ,  F05D2270/17

    摘要： A compressor airfoil (20) in a gas turbine engine is presented. Opposed pressure and suction sides (32,34) are joined together at chordally opposite leading and trailing edges (36,38). The pressure and suction sides (32,34) extend in a span direction from a root (25) to a tip (27) of the airfoil (20). A leading edge sweep angle (α) is defined relative to a tangent to the airfoil (20) and flow velocity vector at a point on the leading edge (36). A leading edge dihedral angle (β) is defined relative to the tangent to the airfoil (20) and a vertical at the point on the leading edge (36). A ratio of the leading edge sweep angle (α) to the leading edge dihedral angle (β) is smaller than 1. A method of forming such airfoil is also presented.

    摘要翻译： 提出了一种燃气涡轮发动机中的压缩机翼型件（20）。 相反的压力和吸力侧（32,34）在弦向相反的前缘和后缘（36,38）处连接在一起。 压力和吸力侧（32,34）在跨度方向从翼型件（20）的根部（25）延伸到尖端（27）。 相对于翼型件（20）的切线和前缘（36​​）上的点处的流速矢量定义前缘扫掠角（±）。 前缘二面角（²）相对于翼型件（20）的切线和在前缘（36​​）上的点处的垂直线限定。 前缘扫掠角（±）与前缘二面角（²）的比值小于1.还提出了形成这种翼型的方法。