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    Centrifugal impeller for gas turbine engine
    1.
    发明授权
    Centrifugal impeller for gas turbine engine 有权

    公开(公告)号：US11125154B2

    公开(公告)日：2021-09-21

    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 ,  F01D5/04 ,  F01D5/12 ,  F04D29/24 ,  F04D29/30 ,  F04D29/28

    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
    5.
    发明授权
    Fan rotor with flow induced resonance control 有权

    公开(公告)号：US11035385B2

    公开(公告)日：2021-06-15

    申请号：US16591876

    申请日：2019-10-03

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Ignatius Theratil ,  Krishna Balike

    IPC: F04D29/66 ,  F04D29/32 ,  F01D5/16 ,  F01D5/14 ,  F04D29/38 ,  B64D27/20

    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 defining a removed portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 20% and 50% of the total span length. The selected natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 5t″ natural vibration mode.

    Fan rotor with flow induced resonance control
    6.
    发明授权
    Fan rotor with flow induced resonance control 有权

    公开(公告)号：US10458436B2

    公开(公告)日：2019-10-29

    申请号：US15465792

    申请日：2017-03-22

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Ignatius Theratil ,  Krishna Balike

    IPC: F04D29/66 ,  F04D29/32 ,  F04D29/38 ,  F01D5/14 ,  F01D5/16 ,  F02K3/06

    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 selected 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 selected 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.

    Controlled gap seal with surface discontinuities
    8.
    发明授权
    Controlled gap seal with surface discontinuities 有权

    公开(公告)号：US11156294B2

    公开(公告)日：2021-10-26

    申请号：US16204367

    申请日：2018-11-29

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Ignatius Theratil ,  Aldo Abate

    IPC: F16J15/44 ,  F01D11/00 ,  F01D11/02 ,  F01D11/06

    Abstract: There is disclosed a controlled gap seal for a gas turbine engine including a ring configured to be in a sealing engagement with a housing and a runner configured for rotation relative to the ring about the central axis. The runner has a runner face facing a ring face of the ring. The ring face is spaced apart from the runner face by a gap. A plurality of surface discontinuities are circumferentially distributed around the central axis on the runner face and/or the ring face. The plurality of surface discontinuities are spaced relative to one another such that a first set of adjacent surface discontinuities are circumferentially spaced from each other at a different distance than a second set of adjacent surface discontinuities. A method of using the controlled gap seal is disclosed.

    Bearing housing with baffles
    9.
    发明授权
    Bearing housing with baffles 有权

    公开(公告)号：US10968774B2

    公开(公告)日：2021-04-06

    申请号：US16196464

    申请日：2018-11-20

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Ignatius Theratil ,  Aldo Abate ,  Nicola Houle

    IPC: F01D25/16 ,  F16C33/72 ,  F02C7/06

    Abstract: There is disclosed an assembly for a gas turbine engine that includes a bearing housing circumferentially extending around a central axis thereof and delimiting a bearing cavity for receiving a bearing therein. A controlled gap seal is secured to the bearing housing, the controlled gap seal including a ring and a runner, the runner rotatable relative to the ring about the central axis, the runner spaced apart from the ring by a gap. The gap defines a fluid passage between the bearing cavity and an environment outside the bearing cavity. At least one baffle is secured to a surface of the bearing housing oriented toward the bearing cavity. The at least one baffle is a fin protruding from the surface and extending into the bearing cavity. The at least one baffle disrupts a cylindricality of the surface. A method of operating the bearing assembly is also disclosed.

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