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    Methods for forming oxide dispersion-strengthened alloys
    22.
    发明授权
    Methods for forming oxide dispersion-strengthened alloys 有权
    形成氧化物分散强化合金的方法

    公开(公告)号：US09447484B2

    公开(公告)日：2016-09-20

    申请号：US14043994

    申请日：2013-10-02

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Harry Lester Kington ,  Donald G. Godfrey ,  Mark C. Morris ,  Michael G. Volas ,  Brian Hann ,  Robert J. Dawson

    IPC: B22F3/105 ,  B22F5/00 ,  B22F5/04 ,  C22C1/04 ,  C22C1/10 ,  C22C32/00 ,  B22F9/08

    CPC classification number: C22C1/0491 ,  B22F3/1055 ,  B22F5/04 ,  B22F9/082 ,  C22C1/10 ,  C22C32/0026 ,  Y02P10/295

    Abstract: In accordance with an exemplary embodiment, a method of forming a oxide dispersion-strengthened alloy metal includes the steps of providing, in a powdered form, an oxide dispersion-strengthened alloy composition that is capable of achieving a dispersion-strengthened microstructure, directing a low energy density energy beam at a portion of the alloy composition, withdrawing the energy beam from the portion of the powdered alloy composition, and cooling the portion of the powdered alloy composition at a rate greater than or equal to about 106° F. per second, thereby forming the oxide dispersion-strengthened alloy metal.

    Abstract translation: 根据示例性实施例，形成氧化物分散强化合金金属的方法包括以粉末形式提供能够实现分散强化微结构的氧化物分散强化合金组合物的步骤， 在合金组合物的一部分处的能量密度能量束，从粉末状合金组合物的部分中取出能量束，并以大于或等于约106°F /秒的速率冷却粉末状合金组合物的该部分， 从而形成氧化物分散强化合金金属。

    FORWARD-SWEPT IMPELLERS AND GAS TURBINE ENGINES EMPLOYING THE SAME
    23.
    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。

    ELECTROSTATIC CHARGE CONTROL INLET PARTICLE SEPARATOR SYSTEM
    24.
    发明申请
    ELECTROSTATIC CHARGE CONTROL INLET PARTICLE SEPARATOR SYSTEM 有权
    静电充电控制入口颗粒分离系统

    公开(公告)号：US20150198090A1

    公开(公告)日：2015-07-16

    申请号：US14154428

    申请日：2014-01-14

    Applicant: Honeywell International Inc.

    Inventor： Jeff Howe ,  Harry Lester Kington ,  Nick Nolcheff

    IPC: F02C7/052 ,  B03C3/41

    CPC classification number: F02C7/052 ,  B03C3/08 ,  B03C3/12 ,  B03C3/361 ,  B03C3/41 ,  B03C2201/10 ,  B64D2033/0246 ,  F05D2260/607 ,  F23R3/04 ,  Y02T50/675

    Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.

    Abstract translation: 用于发动机的入口颗粒分离器系统包括内部流路部分，外部流路部分，分流器，第一静电放电装置和第二静电放电装置。 外部流路部分围绕内部流路部分的至少一部分并且与其间隔开以限定具有空气入口的通道。 分流器设置在空气入口的下游并延伸到通道中，以将通道分成清流流动路径和发动机流动路径。 第一静电充电装置设置在空气入口和分流器之间，并被静电充电至第一极性。 第二静电充电装置设置在第一静电充电装置的下游，并被静电充电至与第一极性相反的第二极性。

    STATIONARY AIRFOILS CONFIGURED TO FORM IMPROVED SLIP JOINTS IN BI-CAST TURBINE ENGINE COMPONENTS AND THE TURBINE ENGINE COMPONENTS INCLUDING THE SAME
    25.
    发明申请
    STATIONARY AIRFOILS CONFIGURED TO FORM IMPROVED SLIP JOINTS IN BI-CAST TURBINE ENGINE COMPONENTS AND THE TURBINE ENGINE COMPONENTS INCLUDING THE SAME 有权
    配置用于形成改进的双缸涡轮发动机部件中的滑动接头和包括其的涡轮发动机部件的固定式空气

    公开(公告)号：US20150159495A1

    公开(公告)日：2015-06-11

    申请号：US14099218

    申请日：2013-12-06

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Harry Lester Kington ,  Shezan Kanjiyani ,  Natalie Wali ,  John Gintert ,  Bradley R. Tucker

    IPC: F01D9/04

    CPC classification number: F01D9/042 ,  B22C9/04 ,  B22C9/22 ,  F01D9/041 ,  F01D25/26 ,  F05D2230/21 ,  F05D2300/50212

    Abstract: Stationary airfoils configured to form an improved slip joint in bi-cast turbine engine components and the turbine engine components including the same are provided. The stationary airfoil for a bi-cast turbine engine component comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. An end portion is shaped with a pair of opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component and to define an interlocking feature. The slip joint permits radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction.

    Abstract translation: 提供了构造成在双流型涡轮发动机部件中形成改进的滑动关节的固定翼型件以及包括其的涡轮发动机部件。 用于双流型涡轮发动机部件的固定翼片包括通过压力侧壁和吸力侧壁互连的前缘和后缘。 端部形成有一对相对的凸缘，以在双流型涡轮发动机部件中形成具有护罩环的滑动接头并且限定互锁特征。 滑动接头允许固定翼型件相对于护罩环由于热差膨胀和收缩而径向移动。

    SYSTEM AND METHOD FOR PREVENTING ICE CRYSTAL ACCRETION IN GAS TURBINE ENGINES
    26.
    发明申请
    SYSTEM AND METHOD FOR PREVENTING ICE CRYSTAL ACCRETION IN GAS TURBINE ENGINES 有权
    用于防止燃气涡轮发动机中的冰晶体收缩的系统和方法

    公开(公告)号：US20150040577A1

    公开(公告)日：2015-02-12

    申请号：US14014560

    申请日：2013-08-30

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Dave Dischinger ,  Ronald Goodwin ,  Harry Lester Kington

    IPC: F02C7/00

    CPC classification number: F02C7/00 ,  F02C7/047 ,  F05D2260/231 ,  F05D2270/311 ,  F05D2270/312 ,  F05D2270/313 ,  Y02T50/675

    Abstract: A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.

    Abstract translation: 一种操作发动机防冰系统的系统和方法包括将一个或多个热源的热量提供给燃气涡轮发动机上或其内的一个或多个组件，感测代表与冰晶体积累相关的一个或多个参数的数据，以及基于 在数据上，至少选择性地抑制一个或多个热源中的至少一个选择的热源向燃气涡轮发动机内部或内部的一个或多个组件中的至少选定的一个供应热量。

    TURBINE STATOR AIRFOILS WITH INDIVIDUAL ORIENTATIONS
    27.
    发明申请
    TURBINE STATOR AIRFOILS WITH INDIVIDUAL ORIENTATIONS 有权
    具有个体定位的涡轮机定子机构

    公开(公告)号：US20130216368A1

    公开(公告)日：2013-08-22

    申请号：US13887801

    申请日：2013-05-06

    Applicant: Honeywell International Inc.

    Inventor： Mark C. Morris ,  Harry Lester Kington ,  James Neumann

    IPC: F01D9/00

    CPC classification number: F01D9/00 ,  F01D5/284 ,  F01D9/041 ,  F05D2300/606 ,  Y02T50/673

    Abstract: In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations.

    Abstract translation: 根据示例性实施例，涡轮机定子部件包括第一端壁; 第二端壁 耦合在第一和第二端壁之间的第一定子翼型件; 以及与第一翼型件相邻并且连接在第一和第二端壁之间的第二定子翼型件。 第一定子翼型件具有第一晶体初级和次级取向。 第二定子翼型具有第二晶体初级和次级取向，第一晶体初级和次级取向不同于第二晶体初级和次级取向。

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