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    Grooved rotor casing system using additive manufacturing method
    13.
    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.

    Variable vane devices containing rotationally-driven translating vane structures and methods for the production thereof
    15.
    发明授权
    Variable vane devices containing rotationally-driven translating vane structures and methods for the production thereof 有权

    公开(公告)号：US11015614B2

    公开(公告)日：2021-05-25

    申请号：US16656211

    申请日：2019-10-17

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Richard David Conner ,  Bruce David Reynolds ,  Timothy Gentry ,  Peter Hall

    IPC: F04D29/56 ,  F01D17/16 ,  F01D9/04 ,  F04D27/00 ,  F04D29/02 ,  F04D29/54 ,  F04D29/64 ,  F01D11/00

    Abstract: Variable vane devices containing rotationally-driven translating vane structures are provided, as are methods for fabricating variable vane devices. In one embodiment, the variable vane device includes a flow assembly having a centerline, an annular flow passage extending through the flow assembly, cam mechanisms, and rotationally-driven translating vane structures coupled to the flow assembly and rotatable relative thereto. The translating vane structures include vane bodies positioned within the annular flow passage and angularly spaced about the centerline. During operation of the variable vane device, the cam mechanisms adjust translational positions of the vane bodies within the annular flow passage in conjunction with rotation of the translating vane structures relative to the flow assembly. By virtue of the translational movement of the translating vane structures, a reduction in the clearances between the vane bodies and neighboring flow assembly surfaces can be realized to reduce end gap leakage and boost device performance.

    COMPRESSOR SECTION OF GAS TURBINE ENGINE INCLUDING SHROUD WITH SERRATED CASING TREATMENT
    16.
    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.

    VARIABLE STATOR VANE ASSEMBLIES AND VARIABLE STATOR VANES THEREOF HAVING A LOCALLY SWEPT LEADING EDGE AND METHODS FOR MINIMIZING ENDWALL LEAKAGE THEREWITH
    18.
    发明申请
    VARIABLE STATOR VANE ASSEMBLIES AND VARIABLE STATOR VANES THEREOF HAVING A LOCALLY SWEPT LEADING EDGE AND METHODS FOR MINIMIZING ENDWALL LEAKAGE THEREWITH 有权
    可变定位器组件及其具有局部切换导向边缘的可变定位器，以及用于最小化其末端泄漏的方法

    公开(公告)号：US20160076548A1

    公开(公告)日：2016-03-17

    申请号：US14485163

    申请日：2014-09-12

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Bruce David Reynolds ,  Timothy Gentry ,  Richard David Conner

    IPC: F04D27/00 ,  F04D29/08 ,  F04D19/00 ,  F04D29/60

    CPC classification number: F04D29/544 ,  F01D5/141 ,  F01D11/005 ,  F01D17/162 ,  F04D29/563 ,  F05D2240/121 ,  F05D2250/70 ,  Y02T50/673

    Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge includes a local forward sweep at the root, a local aft sweep at the tip, or both, thereby forming a locally swept leading edge thereat. The button forward edge portion of one or both of the inner and outer buttons is substantially coextensive with the locally swept leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.

    Abstract translation: 提供具有局部扫掠前缘的可变定子叶片组件和定子叶片。 可变定子叶片包括设置在围绕旋转轴线居中的间隔开的内部和外部按钮之间的翼型件。 内按钮和外按钮均具有按钮前边缘部分。 机翼包括前缘和后缘，压力和吸力侧，以及根部和尖端。 前缘包括根部的局部向前扫掠，尖端处的局部后掠，或两者，从而在那里形成局部扫掠的前缘。 内按钮和外按钮中的一个或两个的按钮前边缘部分与局部扫掠的前缘基本上共同延伸。 还提供了使用其来减小可变定子叶片组件中的端壁泄漏的方法。

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