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    Compressor section of gas turbine engine including shroud with serrated casing treatment
    2.
    发明授权
    Compressor section of gas turbine engine including shroud with serrated casing treatment 有权

    公开(公告)号：US11015465B2

    公开(公告)日：2021-05-25

    申请号：US16363117

    申请日：2019-03-25

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Bruce David Reynolds ,  John Repp ,  David Richard Hanson ,  Nick Nolcheff ,  Darrell K James

    IPC: F01D9/04 ,  F04D29/68 ,  F04D29/52

    Abstract: A compressor section includes a shroud surface and a rotor with a blade tip that opposes the shroud surface. The rotor is configured to rotate within the shroud about an axis of rotation. Moreover, the compressor section includes a serration groove that is recessed into the shroud surface. The serration groove includes a forward portion with a forward transition and a forward surface that faces in the downstream direction. The forward transition is convexly contoured between the shroud surface and the forward surface. The serration groove includes a trailing portion with a taper surface and a trailing transition. The taper surface tapers inward as the taper surface extends from the forward surface to the trailing transition. The trailing transition is convexly contoured between the taper surface and the shroud surface.

    GAS TURBINE ENGINE WITH COMPRESSOR BLEED SYSTEM FOR COMBUSTOR START ASSIST
    7.
    发明申请
    GAS TURBINE ENGINE WITH COMPRESSOR BLEED SYSTEM FOR COMBUSTOR START ASSIST 有权

    公开(公告)号：US20230122939A1

    公开(公告)日：2023-04-20

    申请号：US17450840

    申请日：2021-10-14

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Bruce David Reynolds ,  Nick Nolcheff ,  Mahmoud Mansour ,  Timothy Darling ,  Ernest Kurschat

    IPC: F04D17/02 ,  F01D19/00 ,  F01D17/26 ,  F02C9/18 ,  F02C7/264

    Abstract: A gas turbine engine includes a combustor having a combustor air inlet, an axial-centrifugal compressor, a shroud, a secondary flow duct, and a valve. The shroud surrounds at least a portion of the axial-centrifugal compressor and has a surge bleed plenum defined therein that is in fluid communication with, and receives compressed air from, the axial compressor outlet. The secondary airflow duct has a duct inlet that is in fluid communication with the surge bleed plenum, and a duct outlet that is in fluid communication with the combustor air inlet. The valve is mounted on the secondary airflow duct and is movable between a closed position, in which the secondary airflow duct does not provide fluid communication between the surge bleed plenum and the combustor air inlet, and an open position, in which the secondary airflow duct provides fluid communication between the surge bleed plenum and the combustor air inlet.

    Characteristic distribution for rotor blade of booster rotor
    8.
    发明授权
    Characteristic distribution for rotor blade of booster rotor 有权

    公开(公告)号：US11371354B2

    公开(公告)日：2022-06-28

    申请号：US16892152

    申请日：2020-06-03

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Nick Nolcheff ,  John Repp ,  Bruce Reynolds ,  John Gunaraj

    IPC: F01D5/14

    Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil having a leading edge, a trailing edge and a mean camber line. The airfoil has a delta inlet blade angle defined as a difference between a local inlet blade angle defined in a spanwise location, and a root inlet blade angle defined at the root. The delta inlet blade angle decreases in the spanwise direction from the root to a minimum value at greater than 10% span and from the minimum value, the delta inlet blade angle increases to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft or the fan.

    Grooved shroud casing treatment for high pressure compressor in a turbine engine
    9.
    发明授权
    Grooved shroud casing treatment for high pressure compressor in a turbine engine 有权

    公开(公告)号：US11098731B2

    公开(公告)日：2021-08-24

    申请号：US16732507

    申请日：2020-01-02

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Timothy Gentry ,  Bruce David Reynolds ,  Nick Nolcheff

    IPC: F04D29/52 ,  F01D11/12 ,  F01D5/20 ,  F04D29/16 ,  F04D29/32 ,  F04D29/68 ,  F01D11/08 ,  F02C3/04

    Abstract: A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord positon within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.

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