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    MISTUNED ROTOR FOR GAS TURBINE ENGINE
    12.
    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
    13.
    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。

    CENTRIFUGAL IMPELLER FOR GAS TURBINE ENGINE
    14.
    发明申请
    CENTRIFUGAL IMPELLER FOR GAS TURBINE ENGINE 有权

    公开(公告)号：US20210123378A1

    公开(公告)日：2021-04-29

    申请号：US16674368

    申请日：2019-11-05

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Jason NICHOLS ,  Ignatius THERATIL ,  Mohammadreza AMIRALAEI

    IPC: F02C3/10 ,  F02C7/264

    Abstract: The centrifugal impeller can have a hub and a plurality of blades, each of the blades having a span extending from the hub to a tip edge, camber lines extending from an inlet edge to an outlet edge between two opposite faces, including a tip camber line extending along the tip edge and a 50% span camber line extending at 50% of the span, a thickness extending between opposite faces of each blade, the tip edge having, at a location corresponding to 5% of the tip camber line, less than 15% of the maximum thickness, each of the blades having, along the 50% span camber line, a thickness reaching at least 58% of the maximum thickness and then reducing by at least 5% of the maximum thickness within 10% of the length of the 50% span camber line.

    FAN ROTOR WITH FLOW INDUCED RESONANCE CONTROL
    15.
    发明申请
    FAN ROTOR WITH FLOW INDUCED RESONANCE CONTROL 审中-公开

    公开(公告)号：US20200040914A1

    公开(公告)日：2020-02-06

    申请号：US16587643

    申请日：2019-09-30

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Ignatius THERATIL ,  Krishna BALIKE

    IPC: F04D29/66 ,  F04D29/32 ,  F04D29/38 ,  F01D5/14 ,  F01D5/16

    Abstract: A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 50% and 90% of the total span length. The natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 4th natural vibration mode.

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