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    Spring assemblies for use in gas turbine engines and methods for their manufacture
    76.
    发明授权
    Spring assemblies for use in gas turbine engines and methods for their manufacture 有权
    用于燃气涡轮发动机的弹簧组件及其制造方法

    公开(公告)号：US09562616B2

    公开(公告)日：2017-02-07

    申请号：US13742210

    申请日：2013-01-15

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Laurie Strom ,  Donald G. Godfrey ,  Harry Lester Kington ,  Douglas Hall ,  Mark C. Morris

    IPC: B21F35/00 ,  F16K17/04 ,  B22F3/105 ,  F16F1/04 ,  B22F5/00

    CPC classification number: F16K17/048 ,  B22F3/1055 ,  B22F5/009 ,  B33Y80/00 ,  F01D17/00 ,  F02C7/232 ,  F02C9/38 ,  F05D2230/31 ,  F16F1/043 ,  F16F1/047 ,  F16F2226/04 ,  Y02P10/295 ,  Y10T29/49412 ,  Y10T137/2705

    Abstract: In accordance with an exemplary embodiment, a method for manufacturing a bypass valve of a turbine engine control system is described. The bypass valve includes a proportional valve and an integrator valve and the integrator valve includes an integrator spring assembly. The method includes forming the integrator spring assembly using an additive manufacturing technique. The integrator spring assembly comprises first and second end portions with a spring portion disposed between the first and second end portions. The first and second end portions and the spring portion are formed as an integral unit without welding or brazing using the additive manufacturing technique. The method further includes assembling the integrator spring assembly, the integrator valve, and the proportional valve into a complete bypass valve assembly.

    Abstract translation: 根据示例性实施例，描述了一种用于制造涡轮发动机控制系统的旁通阀的方法。 旁通阀包括比例阀和积分阀，积分器阀包括积分器弹簧组件。 该方法包括使用添加剂制造技术形成积分器弹簧组件。 积分器弹簧组件包括具有设置在第一和第二端部之间的弹簧部分的第一和第二端部。 使用添加剂制造技术，第一和第二端部和弹簧部分形成为不用焊接或钎焊的整体单元。 该方法还包括将积分器弹簧组件，积分器阀和比例阀组装成完整的旁通阀组件。

    Gas turbine engine components with blade tip cooling
    77.
    发明授权
    Gas turbine engine components with blade tip cooling 有权
    燃气涡轮发动机部件采用叶片冷却

    公开(公告)号：US09546554B2

    公开(公告)日：2017-01-17

    申请号：US13629284

    申请日：2012-09-27

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Daniel Cregg Crites ,  Steve Halfmann ,  Mark C. Morris ,  Ardeshir Riahi

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit.

    Abstract translation: 提供了一种用于发动机的涡轮机部分的涡轮机转子叶片。 转子叶片包括平台和从平台延伸到涡轮部分的主流气体路径中的翼型件。 翼型件包括压力侧壁，在前缘和后缘处连接到压力侧壁的吸力侧壁和在吸力侧壁和压力侧壁之间延伸的尖端盖。 转子叶片还包括内部冷却回路，其具有构造成将冷却空气输送到顶盖的顶端通道和位于内部冷却回路的顶端通道内的流动加速器。

    TURBINE ENGINE COUPLINGS AND METHODS FOR MANUFACTURING TURBINE ENGINE COUPLINGS
    78.
    发明申请
    TURBINE ENGINE COUPLINGS AND METHODS FOR MANUFACTURING TURBINE ENGINE COUPLINGS 有权
    涡轮发动机联轴器和制造涡轮发动机联轴器的方法

    公开(公告)号：US20170009604A1

    公开(公告)日：2017-01-12

    申请号：US14793465

    申请日：2015-07-07

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Mark C. Morris ,  David R. Waldman ,  Donald G. Godfrey G. Godfrey ,  Brian G. Baughman ,  Mark McNair ,  Justin C. Mickelsen

    IPC: F01D25/28

    CPC classification number: F01D25/28 ,  B22F3/1055 ,  B33Y80/00 ,  F02C7/32 ,  F02K1/80 ,  F16L27/111 ,  F16L47/18 ,  Y02P10/295

    Abstract: A coupling apparatus for use in sealingly connecting a first fluid flow path to a second fluid flow path. The coupling apparatus includes a rigid fluid flow channel having a first end and a second end, wherein the fluid flow channel is substantially rigid in an axial direction and a radial direction, a first sealing terminus that is rigidly connected to the first end and that is configured for sealing with the first fluid flow path, and a second sealing terminus that is slidingly disposed about the second end such that the second sealing terminus is configured for relative movement with respect to the second end, and wherein the second sealing terminus is further configured for sealing with the second fluid flow path. The coupling apparatus further includes a flexible coupler connected to both the first sealing terminus and the second sealing terminus and surrounding the fluid flow channel, wherein the coupler is relatively more flexible in the axial direction and the radial direction as compared to the fluid flow channel.

    Abstract translation: 一种用于将第一流体流动路径密封地连接到第二流体流动路径的联接装置。 联接装置包括具有第一端和第二端的刚性流体流动通道，其中流体流动通道在轴向方向和径向方向上基本上是刚性的，第一密封末端刚性地连接到第一端，也就是 构造成用于与第一流体流动路径密封，以及第二密封端，其围绕第二端滑动地设置，使得第二密封端被配置为相对于第二端相对运动，并且其中第二密封末端进一步配置 用于与第二流体流动路径密封。 联接装置还包括连接到第一密封末端和第二密封末端两端并围绕流体流动通道的柔性连接器，其中耦合器在与流体流动通道相比在轴向方向和径向上相对更柔性。

    Gas turbine engine components and methods for their manufacture using additive manufacturing techniques
    79.
    发明授权
    Gas turbine engine components and methods for their manufacture using additive manufacturing techniques 有权
    燃气涡轮发动机组件及其使用添加剂制造技术制造的方法

    公开(公告)号：US09429023B2

    公开(公告)日：2016-08-30

    申请号：US13740422

    申请日：2013-01-14

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Donald G. Godfrey ,  Mark C. Morris ,  Andy Szuromi

    IPC: F01D5/14 ,  B22F3/105 ,  B22F5/00 ,  B22F5/04

    CPC classification number: F01D5/14 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  Y02P10/295 ,  Y10T29/49316

    Abstract: In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3D design model for the component, adding one or more crack resistant features to the 3D design model of the component to produce an enhanced design model, and manufacturing the component using an additive manufacturing technique in accordance with the enhanced design model. The one or more crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured component.

    Abstract translation: 根据示例性实施例，使用添加剂制造技术制造部件的方法包括为部件提供3D设计模型，向组件的3D设计模型添加一个或多个抗裂特征以产生增强的设计模型，以及 使用添加剂制造技术根据增强的设计模型制造组件。 提供一个或多个抗裂特征以减少或消除所制造的部件中的裂纹的发生。

    Gas turbine engines with turbine airfoil cooling
    80.
    发明授权
    Gas turbine engines with turbine airfoil cooling 有权
    带涡轮翼型冷却的燃气涡轮发动机

    公开(公告)号：US09394798B2

    公开(公告)日：2016-07-19

    申请号：US13855417

    申请日：2013-04-02

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Daniel Cregg Crites ,  Mark C. Morris ,  Lorenzo Crosatti ,  Ardeshir Riahi

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2260/201 ,  Y02T50/671 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.

    Abstract translation: 提供了一种用于燃气涡轮发动机的翼型件。 翼型件包括具有前缘的主体，后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。 身体定义一个内腔。 所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸的内壁，以限定供应室和前缘室。 内壁限定具有基部和局部延伸部分的冷却孔，以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。

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