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    COMPRESSOR SHROUD WITH SHROUD SEGMENTS
    11.
    发明申请
    COMPRESSOR SHROUD WITH SHROUD SEGMENTS 审中-公开

    公开(公告)号：US20200256205A1

    公开(公告)日：2020-08-13

    申请号：US16271179

    申请日：2019-02-08

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Tibor URAC ,  Barry BARNETT

    IPC: F01D9/04

    Abstract: There is disclosed a shroud for a compressor stator, including: shroud segments extending circumferentially around an axis along portions of a circumference of the shroud. At least one of the shroud segments extending from a first lateral edge to a second lateral edge. The shroud segment has an inner face oriented toward the axis and an opposed outer face oriented away from the axis. At least one opening extends from the inner face to the outer face for receiving a vane of the compressor. A tab protrudes circumferentially from the second lateral edge and away from the first lateral edge. A slot extends circumferentially from the first lateral edge toward the second lateral edge. The tab is matingly received within a slot of an adjacent one of the shroud segments.

    MISTUNED ROTOR FOR GAS TURBINE ENGINE
    13.
    发明申请
    MISTUNED ROTOR FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20190085704A1

    公开(公告)日：2019-03-21

    申请号：US15706247

    申请日：2017-09-15

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Thomas VEITCH ,  Farid ABRARI ,  Ernest ADIQUE ,  Daniel FUDGE ,  Kari HEIKURINEN ,  Paul STONE ,  Ignatius THERATIL ,  Peter TOWNSEND ,  Tibor URAC

    IPC: F01D5/16 ,  F01D5/14

    Abstract: A rotor for a gas turbine engine. The rotor includes blades circumferentially distributed around a hub. The blades have airfoils with a span defined between a root and tip, a chord defined between a leading edge and a trailing edge, and a thickness defined between a pressure side surface and suction side surface. The blades include first blades and second blades. The airfoil of the first blades has a first thickness distribution defining a first natural vibration frequency of the airfoils of the first blades. The airfoil of the second blades has a second thickness distribution defining a second natural vibration frequency different than the first natural vibration frequency. The first thickness distribution is different than the second thickness distribution along a radially-inner half of the span, and the first thickness distribution matches the second thickness distribution along a radially-outer half of the span.

    GAS TURBINE ENGINE ROTOR CASING TREATMENT
    14.
    发明申请
    GAS TURBINE ENGINE ROTOR CASING TREATMENT 审中-公开
    气体涡轮发动机转子油箱处理

    公开(公告)号：US20160305285A1

    公开(公告)日：2016-10-20

    申请号：US14686010

    申请日：2015-04-14

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Tibor URAC ,  Peter TOWNSEND ,  Ignatius THERATIL

    IPC: F01D25/24 ,  F01D25/00

    CPC classification number: F04D29/685

    Abstract: An annular casing for a rotor of a gas turbine engine includes a casing treatment having at least one groove defined in the annular casing wall with an open end defined in an inner surface of the annular casing wall, and a perforated sheet overlapping the open end of the at least one groove. The perforated sheet includes a plurality of apertures therethrough in fluid communication with the at least one groove. A method of reducing flow losses through a flow path having a rotor with a plurality of rotating blades extending therethrough is also presented.

    Abstract translation: 用于燃气涡轮发动机的转子的环形壳体包括壳体处理，其具有限定在环形壳体壁中的至少一个凹槽，限定在环形壳体壁的内表面中的开口端，以及与孔的开口端重叠的穿孔板 所述至少一个凹槽。 穿孔板包括通过其与至少一个槽流体连通的多个孔。 还提出了一种通过具有带有延伸穿过其中的多个旋转叶片的转子的流路减小流动损失的方法。

    INNER SHROUD ASSEMBLY FOR STATOR VANES
    17.
    发明申请
    INNER SHROUD ASSEMBLY FOR STATOR VANES 审中-公开

    公开(公告)号：US20200300101A1

    公开(公告)日：2020-09-24

    申请号：US16672023

    申请日：2019-11-01

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Tibor URAC ,  Barry BARNETT ,  Matthew MESCHINO

    IPC: F01D5/30

    Abstract: A gas turbine engine assembly comprises a casing defining a gas path, the casing including a shroud having an annular body having a surface defining a portion of gas path, the shroud having slots configured for receiving inserted vanes. The slots are delimited substantially about their perimeter by respective flanges, the flanges radially offset from the shroud gas path surface so as to be disposed outside of said gas path, the flanges defined by opposed flange surfaces. Vanes received in the slots. Grommets engage the vanes at the slots. Inserts extend between the shroud and the grommets, the inserts having slots configured for engaging both of the opposed flanges, the inserts extending in a radial direction from at least the respective flange to an adjacent said shroud gas path surface to substantially matchingly mate with an inner surface the adjacent shroud gas path surface.

    TURBOFAN NACELLE ASSEMBLY WITH FLOW DISRUPTOR
    20.
    发明申请
    TURBOFAN NACELLE ASSEMBLY WITH FLOW DISRUPTOR 审中-公开

    公开(公告)号：US20180187697A1

    公开(公告)日：2018-07-05

    申请号：US15399343

    申请日：2017-01-05

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Tibor URAC ,  Peter TOWNSEND

    IPC: F04D29/54 ,  F01D25/24 ,  F04D19/00 ,  F01D9/04 ,  F04D29/52

    Abstract: A turbofan engine is disclosed which includes a nacelle assembly, having an interior surface for directing airflow, and a flow disruptor positioned on the interior surface upstream of the fan, the flow disruptor extending towards the axis a height greater than the anticipated boundary layer height of the airflow. A turbofan engine which includes an array of circumferentially disposed flow disruptors extending from a fan case inner surface is also disclosed. A method of mitigating fan flutter in a gas turbine engine by generating a circumferential asymmetrically in the airflow, upstream of the fan, is also described.

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