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    BEARING COMPARTMENT OIL AUTO-IGNITION MITIGATION
    31.
    发明申请
    BEARING COMPARTMENT OIL AUTO-IGNITION MITIGATION 审中-公开

    公开(公告)号：US20200080478A1

    公开(公告)日：2020-03-12

    申请号：US16127365

    申请日：2018-09-11

    Applicant: United Technologies Corporation

    Inventor： Daniel S. Rogers ,  Taryn Narrow ,  Gregory E. Reinhardt ,  Collin P. Fitzgerald ,  Christopher M. Valva ,  Leonard Kolshak

    IPC: F02C7/06

    Abstract: A bearing assembly for a gas turbine engine includes, among other things, a bearing housing extending along an axis to define a bearing compartment, a lubricant seal assembly adjacent to the bearing housing to bound the bearing compartment, an air seal assembly defining a vent cavity along the bearing housing, wherein a mixing cavity is defined between the lubricant seal assembly and the air seal assembly, and wherein the bearing housing defines an airflow supply passage, an airflow vent passage and a scupper passage having respective fluid ports at different circumferential positions relative to the axis, the fluid port of the airflow vent passage fluidly coupled to the vent cavity, and the fluid ports of the airflow supply and scupper passages fluidly coupled to the mixing cavity. A method of sealing for a gas turbine engine is also disclosed.

    Gas turbine engine assembly method and system
    32.
    发明授权
    Gas turbine engine assembly method and system 有权

    公开(公告)号：US10533498B2

    公开(公告)日：2020-01-14

    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

    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.

    Gas turbine engine shaft bearing configuration
    33.
    发明授权
    Gas turbine engine shaft bearing configuration 有权

    公开(公告)号：US10400629B2

    公开(公告)日：2019-09-03

    申请号：US14012576

    申请日：2013-08-28

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Todd A. Davis ,  Gregory E. Reinhardt ,  Enzo DiBenedetto

    IPC: F02C7/06 ,  F01D25/16 ,  F02C7/36 ,  F02K3/04

    Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.

    GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE
    35.
    发明申请
    GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE 审中-公开

    公开(公告)号：US20190107120A1

    公开(公告)日：2019-04-11

    申请号：US16159820

    申请日：2018-10-15

    Applicant: United Technologies Corporation

    Inventor： John C. Ditomasso ,  Gregory E. Reinhardt

    IPC: F04D29/54 ,  F01D25/24 ,  F04D29/64

    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
    37.
    发明授权
    Gas turbine engine assembly method and system 有权

    公开(公告)号：US09885286B2

    公开(公告)日：2018-02-06

    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 ,  B66C11/12 ,  F01D25/28 ,  B66C11/04

    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.

    Airfoil module
    38.
    发明授权
    Airfoil module 有权

    公开(公告)号：US09759078B2

    公开(公告)日：2017-09-12

    申请号：US14606542

    申请日：2015-01-27

    Applicant: United Technologies Corporation

    Inventor： Jorge Farah ,  Gregory E. Reinhardt

    IPC: F01D11/00 ,  F01D9/04

    CPC classification number: F01D11/005 ,  F01D9/04 ,  Y02T50/672

    Abstract: An airfoil module may have an outer diameter ring assembly, a vane assembly having a stator vane and an inner diameter ring assembly. The outer diameter ring assembly and the inner diameter ring assembly may be arranged concentrically with the stator vane of the vane assembly extending between them. The inner diameter ring assembly may have a first inner diameter ring section sealing end and a second inner diameter ring section sealing end. A feather seal may be disposed along the first inner diameter ring section sealing end. A stator ring assembly may comprise multiple airfoil modules arranged in an annulus. The outer diameter ring assemblies may be joined together by brazing or welding, or may share a unified outer diameter ring assembly. The inner diameter ring assemblies may abut feather seals so that the airfoil modules may expand and contract independently along the inner diameter ring assemblies.

    AIRFOIL MODULE
    39.
    发明申请
    AIRFOIL MODULE 有权
    AIRFOIL模块

    公开(公告)号：US20160215641A1

    公开(公告)日：2016-07-28

    申请号：US14606542

    申请日：2015-01-27

    Applicant: United Technologies Corporation

    Inventor： Jorge Farah ,  Gregory E. Reinhardt

    IPC: F01D11/00 ,  F01D9/04

    CPC classification number: F01D11/005 ,  F01D9/04 ,  Y02T50/672

    Abstract: An airfoil module may have an outer diameter ring assembly, a vane assembly having a stator vane and an inner diameter ring assembly. The outer diameter ring assembly and the inner diameter ring assembly may be arranged concentrically with the stator vane of the vane assembly extending between them. The inner diameter ring assembly may have a first inner diameter ring section sealing end and a second inner diameter ring section sealing end. A feather seal may be disposed along the first inner diameter ring section sealing end. A stator ring assembly may comprise multiple airfoil modules arranged in an annulus. The outer diameter ring assemblies may be joined together by brazing or welding, or may share a unified outer diameter ring assembly. The inner diameter ring assemblies may abut feather seals so that the airfoil modules may expand and contract independently along the inner diameter ring assemblies.

    Abstract translation: 翼型模块可以具有外径环组件，具有定子叶片和内径环组件的叶片组件。 外径环组件和内径环组件可以与叶片组件的定子叶片在它们之间延伸同心地布置。 内径环组件可以具有第一内径环部分密封端部和第二内径环形部分密封端部。 羽毛密封件可以沿着第一内径环部密封端部设置。 定子环组件可以包括布置在环形空间中的多个翼型模块。 外径环组件可以通过钎焊或焊接连接在一起，或者可以共享一个统一的外径环组件。 内径环组件可以邻接羽毛密封件，使得翼型件模块可以沿内径环组件独立地膨胀和收缩。

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