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    FORWARD-SWEPT IMPELLERS AND GAS TURBINE ENGINES EMPLOYING THE SAME
    13.
    发明申请
    FORWARD-SWEPT IMPELLERS AND GAS TURBINE ENGINES EMPLOYING THE SAME 有权
    前进式驱动器和使用其的气动涡轮发动机

    公开(公告)号：US20160238018A1

    公开(公告)日：2016-08-18

    申请号：US14623761

    申请日：2015-02-17

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Richard David Conner ,  Michael Todd Barton ,  Yoseph Gebre-Giorgis ,  Harry Lester Kington ,  John Repp

    IPC: F04D29/28 ,  F01D9/04 ,  F01D5/22 ,  F04D29/32

    CPC classification number: F04D29/284 ,  F01D5/225 ,  F01D9/04 ,  F02C3/09 ,  F05D2250/38 ,  F05D2260/941 ,  Y02T50/671

    Abstract: Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft. The forward-swept impeller includes, in turn, an inboard impeller section, an outboard impeller section circumscribing the inboard impeller section, and a plurality of hub flow paths extending over the forward-swept impeller from the inboard impeller section to the outboard impeller section. The plurality of hub flow paths each have a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit.

    Abstract translation: 如同包含前掠式叶轮的燃气涡轮发动机的实施例一样，提供了前掠式叶轮的实施例。 在一个实施例中，燃气涡轮发动机包括安装在轴上的轴和向前扫掠的叶轮。 前掠式叶轮又包括内侧叶轮部分，外侧叶轮部分，其包围内侧叶轮部分，以及多个轮毂流动路径，其沿前掠式叶轮从内侧叶轮部分延伸到外侧叶轮部分。 多个轮毂流动路径各自具有沿着与流路出口相切的直线沿向前方向倾斜的流路出口。

    Grooved rotor casing system using additive manufacturing method
    14.
    发明授权
    Grooved rotor casing system using additive manufacturing method 有权

    公开(公告)号：US11473438B2

    公开(公告)日：2022-10-18

    申请号：US16431368

    申请日：2019-06-04

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Bruce David Reynolds ,  John Repp ,  Peter Hall

    IPC: F01D11/08 ,  F01D25/24 ,  F04D29/52 ,  F01D9/04 ,  F04D27/00

    Abstract: Rotor systems and methods for improved performance with extended range to stall fabricated through the use of additive manufacturing. A rotor has blades that extend to tips and rotates about an axis. A casing fits over the rotor so that the tips are configured to pass proximate the casing when the rotor rotates. The casing channels a flow stream across the rotor. Grooves are defined in the casing and extend longitudinally at an acute angle relative to the axis. The grooves extend a distance upstream from a leading edge of the blades and over at least a portion of the blade tips so that the blade tips are configured to pass across the grooves when the rotor rotates.

    CHARACTERISTIC DISTRIBUTION FOR ROTOR BLADE OF BOOSTER ROTOR
    15.
    发明申请
    CHARACTERISTIC DISTRIBUTION FOR ROTOR BLADE OF BOOSTER ROTOR 有权

    公开(公告)号：US20210381385A1

    公开(公告)日：2021-12-09

    申请号：US16892155

    申请日：2020-06-03

    Applicant: HONEYWELL INTERNATIONAL INC.

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

    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 extending in a spanwise direction from 0% span at a root to 100% span at a tip and having a leading edge and a trailing edge. The airfoil has a plurality of spanwise locations between the root and the tip each having a normalized local maximum thickness. A value of the normalized local maximum thickness decreases from the root to a minimum value and increases from the minimum value to the tip, and the minimum value is within 60% span to 90% span. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to a shaft or a fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and the fan.

    CHARACTERISTIC DISTRIBUTION FOR ROTOR BLADE OF BOOSTER ROTOR
    16.
    发明申请
    CHARACTERISTIC DISTRIBUTION FOR ROTOR BLADE OF BOOSTER ROTOR 有权

    公开(公告)号：US20210381382A1

    公开(公告)日：2021-12-09

    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 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 and the fan.

    COMPRESSOR SECTION OF GAS TURBINE ENGINE INCLUDING SHROUD WITH SERRATED CASING TREATMENT
    18.
    发明申请
    COMPRESSOR SECTION OF GAS TURBINE ENGINE INCLUDING SHROUD WITH SERRATED CASING TREATMENT 审中-公开

    公开(公告)号：US20200308970A1

    公开(公告)日：2020-10-01

    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

    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.

    Core-protecting fan modules and turbofan engines containing the same
    19.
    发明授权
    Core-protecting fan modules and turbofan engines containing the same 审中-公开

    公开(公告)号：US10670040B2

    公开(公告)日：2020-06-02

    申请号：US15439430

    申请日：2017-02-22

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Nick Nolcheff ,  John Repp ,  Jeffrey Hayes ,  John A Gunaraj ,  Yoseph Gebre-Giorgis

    IPC: F04D29/32 ,  F04D29/54 ,  F04D29/34 ,  F01D5/14 ,  F01D5/34 ,  F02K3/06 ,  F01D5/02 ,  F02C7/05 ,  B64D33/02 ,  B64C11/14

    Abstract: Embodiments of a core-protecting fan module are provided, as are embodiments of a turbofan engine containing such a fan module. In an embodiment, the core-protecting fan module contains a nose member, a fan rotor downstream of the nose member, a full span stator downstream of the fan rotor, and a splitter structure downstream of the fan rotor. The fan rotor includes a plurality of fan blades, which extends from a rotor hub and which is angularly spaced about a rotational axis. Certain fundamental angular relationships are observed between the angles formed by rotational axis, the nose member, the fan rotor, and a leading edge of the splitter structure to reduce contaminant ingestion by the core flow path and to promote moisture shedding to reduce susceptibility to icing within the fan module, while further avoiding or minimizing negative impacts to other structural and functional aspects of the turbofan engine.

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