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    Gas turbine engine front center body architecture
    1.
    发明授权
    Gas turbine engine front center body architecture 有权

    公开(公告)号：US10935048B2

    公开(公告)日：2021-03-02

    申请号：US16159820

    申请日：2018-10-15

    Applicant: United Technologies Corporation

    Inventor： John C. Ditomasso ,  Gregory E. Reinhardt

    IPC: F01D25/28 ,  F04D29/54 ,  F01D25/24 ,  F04D29/64 ,  F01D25/16 ,  F02C7/20

    Abstract: In one exemplary embodiment, a center body support for a gas turbine engine includes a fan exit guide vane mounting ring and an outer annular wall. An aft flange extends radially outward from the outer annular wall. An inner annular wall is radially spaced from and structurally interconnected to the outer annular wall by a circumferential array of struts. A brace interconnects the aft flange to a forward portion of the outer annular wall. The aft flange includes inner and outer mounting features spaced radially apart from one another. The inner and outer mounting feature respectively receive first and second sets of fasteners. The forward portion extends in a radially outward direction from the outer annular wall. The forward portion includes a forward mounting feature that receives a third set of fasteners. The outer and forward mounting features are secured to the fan exit guide vane mounting ring respectively by the first and third sets of fasteners. Forward, outer and inner mounting features define a triangular cross-sectional shape. The forward portion has a radial inner end opposite a radial outer end. The brace is joined at the radial outer end. The brace transfers an axial load from the aft flange to the radial outer end of the forward portion.

    GAS TURBINE ENGINE ASSEMBLY METHOD AND SYSTEM
    2.
    发明申请
    GAS TURBINE ENGINE ASSEMBLY METHOD AND SYSTEM 审中-公开

    公开(公告)号：US20180156125A1

    公开(公告)日：2018-06-07

    申请号：US15889259

    申请日：2018-02-06

    Applicant: United Technologies Corporation

    Inventor： Gabrielle Murphy ,  Gregory E. Reinhardt ,  Robert M. Lewis ,  Scott L. Peterson

    IPC: F02C7/20 ,  B66C11/12 ,  B66C11/04 ,  F01D25/28

    CPC classification number: F02C7/20 ,  B66C11/04 ,  B66C11/12 ,  F01D25/285 ,  F05D2230/68 ,  Y10T29/49236

    Abstract: An assembly system for assembling a gas turbine engine including a support beam defining a horizontal plane for assembly of engine components along a horizontal axis substantially parallel with the support beam. A forward arm is supported on the support beam for supporting a forward portion of an engine component. An aft arm is supported on the support beam for supporting an aft portion of the engine component. An aft mounting ring is attachable to an aft end of an engine assembly. A forward mounting ring is attachable to a forward end of the engine assembly. A drive is mounted to the aft arm engageable to the aft mounting ring for rotating the engine assembly about the horizontal axis. A roller is supported on the forward arm and engageable to the forward mounting ring to support the first end of the engine assembly during rotation about the horizontal axis. A method is also disclosed.

    SEAL SUPPORT STRUCTURES FOR TURBOMACHINES
    5.
    发明申请
    SEAL SUPPORT STRUCTURES FOR TURBOMACHINES 有权
    密封支持结构的涡轮机

    公开(公告)号：US20160376925A1

    公开(公告)日：2016-12-29

    申请号：US14662347

    申请日：2015-03-19

    Applicant: United Technologies Corporation

    Inventor： Seth A. Max ,  Anthony P. Cherolis ,  Steven D. Porter ,  Joshua D. Winn ,  Gregory E. Reinhardt ,  Jeffrey J. Lienau

    IPC: F01D25/28 ,  F01D25/24 ,  F01D11/00

    CPC classification number: F01D25/28 ,  F01D11/003 ,  F01D11/006 ,  F01D25/24 ,  F01D25/243 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2240/60 ,  F05D2260/97

    Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.

    Abstract translation: 用于涡轮机的密封支撑结构包括成形为安装到涡轮机的固定结构的安装部分和设置在从安装部分轴向延伸的安装部分上的圆柱形腿部。 圆柱形腿部可以包括径向延伸的凸缘。 凸缘可以从圆柱形腿部的端部以90度的角度延伸。 凸缘可以在轴向方向上至少部分地延伸。 圆筒形腿部可以与安装部一体地形成。 在实施例中，圆柱形腿部不与安装部分成一体，即，圆柱形腿部是与安装部分接合的分离件。

    GAS TURBINE ENGINE ASSEMBLY METHOD AND SYSTEM
    6.
    发明申请
    GAS TURBINE ENGINE ASSEMBLY METHOD AND SYSTEM 有权
    燃气轮机发动机总成方法与系统

    公开(公告)号：US20150361894A1

    公开(公告)日：2015-12-17

    申请号：US14737671

    申请日：2015-06-12

    Applicant: United Technologies Corporation

    Inventor： Gabrielle Murphy ,  Gregory E. Reinhardt ,  Robert M. Lewis ,  Scott L. Peterson

    IPC: F02C7/20

    CPC classification number: F02C7/20 ,  B66C11/04 ,  B66C11/12 ,  F01D25/285 ,  F05D2230/68 ,  Y10T29/49236

    Abstract: An assembly system for assembling a gas turbine engine including a support beam defining a horizontal plane for assembly of engine components along a horizontal axis substantially parallel with the support beam. A forward arm is supported on the support beam for supporting a forward portion of an engine component. An aft arm is supported on the support beam for supporting an aft portion of the engine component. An aft mounting ring is attachable to an aft end of an engine assembly. A forward mounting ring is attachable to a forward end of the engine assembly. A drive is mounted to the aft arm engageable to the aft mounting ring for rotating the engine assembly about the horizontal axis. A roller is supported on the forward arm and engageable to the forward mounting ring to support the first end of the engine assembly during rotation about the horizontal axis. A method is also disclosed.

    Abstract translation: 一种用于组装燃气涡轮发动机的组装系统，其包括限定水平面的支撑梁，用于沿着基本上平行于支撑梁的水平轴线组装发动机部件。 前臂支撑在支撑梁上，用于支撑发动机部件的前部。 后臂支撑在支撑梁上，用于支撑发动机部件的后部。 后安装环可附接到发动机组件的后端。 前安装环可附接到发动机组件的前端。 驱动器安装到后臂上，可与后安装环接合，以使发动机组件围绕水平轴线旋转。 辊子被支撑在前臂上并可与前安装环接合，以在围绕水平轴线旋转期间支撑发动机组件的第一端。 还公开了一种方法。

    Horizontal engine build stand
    9.
    发明授权
    Horizontal engine build stand 有权

    公开(公告)号：US10920621B2

    公开(公告)日：2021-02-16

    申请号：US16250287

    申请日：2019-01-17

    Applicant: United Technologies Corporation

    Inventor： Gabrielle Murphy ,  Robert M. Lewis ,  Gregory E. Reinhardt

    IPC: B23P19/04 ,  F01D25/28 ,  F02C7/20 ,  B64F5/50 ,  B25H1/00 ,  F01D25/16 ,  F01D25/24 ,  F04D29/52

    Abstract: A horizontal support tool for an engine build stand, the horizontal support tool includes a support tube along an axis and a tie shaft between a handle and a puck assembly, the puck assembly including a puck selectively extendable and retractable transverse to the axis in response to rotation of the handle. A method of horizontally assembling a portion of a gas turbine engine including mounting a first module to an engine build stand; installing a horizontal support tool into the first module, the horizontal support tool supported in a spherical bearing supported by the engine build stand; and installing a second module to the first module, the horizontal support tool operable to at least partially support second module.

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