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    SYSTEMS AND METHODS FOR THRUST REVERSER WITH TEMPERATURE AND FLUID MANAGEMENT
    12.
    发明申请
    SYSTEMS AND METHODS FOR THRUST REVERSER WITH TEMPERATURE AND FLUID MANAGEMENT 审中-公开

    公开(公告)号：US20190293022A1

    公开(公告)日：2019-09-26

    申请号：US15927578

    申请日：2018-03-21

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Justin C. Mickelsen ,  Morris Anderson

    IPC: F02K1/76 ,  F02K1/72 ,  F02K1/60

    Abstract: A thrust reverser system for a gas turbine engine includes at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system. The thrust reverser system includes at least one body coupled to the at least one hinge. The at least one body has a first body end and an opposing second body end. The body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end. The body is positioned within the at least one opening based on an operating condition of the gas turbine engine.

    HEAT RESISTANT FASTENING SYSTEMS
    14.
    发明申请
    HEAT RESISTANT FASTENING SYSTEMS 有权

    公开(公告)号：US20170175801A1

    公开(公告)日：2017-06-22

    申请号：US14973148

    申请日：2015-12-17

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Justin C. Mickelsen ,  Aaron Duncan ,  Patrick S. Mulloy

    IPC: F16B43/00

    CPC classification number: F16B43/001 ,  F01D25/243 ,  F02C7/25 ,  F05D2260/31

    Abstract: A heat resistant washer for a heat resistant fastening system and a heat resistant fastening system is provided. The heat resistant washer includes a fire retardant material, and a housing that includes a base and a flange, with a throughbore defined through the base to receive a fastener. The housing defines a cavity adjacent to the throughbore and at least one guide. The fire retardant material is disposed within the cavity and the at least one guide directs the fire retardant material in an active state out of the cavity.

    TURBINE ENGINE COUPLINGS AND METHODS FOR MANUFACTURING TURBINE ENGINE COUPLINGS
    15.
    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。

    NACELLE INLET AND ENGINE FAN HOUSING ASSEMBLY AND METHOD FOR MAKING SAME
    16.
    发明申请
    NACELLE INLET AND ENGINE FAN HOUSING ASSEMBLY AND METHOD FOR MAKING SAME 审中-公开
    NACELLE入口和发动机风扇壳体组件及其制造方法

    公开(公告)号：US20160084108A1

    公开(公告)日：2016-03-24

    申请号：US14494868

    申请日：2014-09-24

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Justin C. Mickelsen ,  Shawn Alstad ,  Mark Knowles ,  Bill Russell Watson

    IPC: F01D25/04 ,  F01D25/24

    CPC classification number: F01D25/04 ,  F01D25/24 ,  F02C7/045 ,  F05D2220/36 ,  F05D2230/53 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2260/96

    Abstract: A system and method is provided for coupling a nacelle inlet assembly to an engine fan housing structure that provides adequate clearance and access for removing a blisk fan from a turbofan engine. This is accomplished by utilizing a nacelle inlet forward compartment, referred to herein as the “D-lip”and an acoustic liner that are inseparable and removable as an integral unit, providing sufficient clearance for removable of the blisk fan. The nacelle inlet assembly may be slidably coupled to the engine fan housing structure, minimizing assembly interfaces and therefore overall aircraft engine weight.

    Abstract translation: 提供了一种用于将机舱入口组件耦合到发动机风扇壳体结构的系统和方法，该发动机风扇壳体结构提供足够的间隙和通路以从涡轮风扇发动机移除叶轮风扇。 这是通过利用这里称为“D唇”的机舱前进舱和作为整体单元不可分离和可拆卸的声学衬垫来实现的，为空挡风扇提供足够的间隙。 机舱入口组件可以可滑动地联接到发动机风扇壳体结构，使组装界面最小化，从而使整个飞机发动机重量最小化。

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