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    ASSEMBLY ALIGNMENT HANDLING DAMAGE TOLERANT SPLINE
    1.
    发明申请
    ASSEMBLY ALIGNMENT HANDLING DAMAGE TOLERANT SPLINE 审中-公开

    公开(公告)号：US20190211881A1

    公开(公告)日：2019-07-11

    申请号：US15864292

    申请日：2018-01-08

    Applicant: United Technologies Corporation

    Inventor： Charles Mayaka ,  Anthony R. Bifulco

    IPC: F16D1/10 ,  F16C3/02 ,  F16D1/02

    CPC classification number: F01D5/026 ,  F05D2230/64 ,  F05D2240/60

    Abstract: Aspects of the disclosure are directed to a gas turbine engine shaft, having an outer circumferential surface that circumscribes a central axis. The gas turbine engine shaft may comprise a plurality of splines extending along a portion of the outer circumferential surface, where each of the plurality of splines comprises an axial face that tapers from the outer circumferential surface to a spline top surface and includes a curved chamfered surface at a radially distal end of the axial face. The plurality of splines may further comprise a first sidewall and a second sidewall separated by a first spline width distance along the outer circumferential surface, where the first and second sidewalls taper inwardly from the outer circumferential surface to a second spline width along the spline top surface where the second spline width distance is less than the first spline width distance.

    Fiber Reinforced Spacer for a Gas Turbine Engine
    5.
    发明申请
    Fiber Reinforced Spacer for a Gas Turbine Engine 审中-公开
    燃气轮机发动机用纤维增强隔板

    公开(公告)号：US20160153463A1

    公开(公告)日：2016-06-02

    申请号：US14929701

    申请日：2015-11-02

    Applicant: United Technologies Corporation

    Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

    IPC: F04D29/32 ,  F01D25/28 ,  F02C3/06 ,  F01D5/02

    CPC classification number: F04D29/321 ,  F01D5/02 ,  F01D5/066 ,  F01D11/001 ,  F01D25/28 ,  F02C3/06 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2300/603 ,  F05D2300/6032 ,  F05D2300/614 ,  Y02T50/672

    Abstract: A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material. As a gas turbine engine operates, the rotation creates forces which can deform, expand, contract or translate certain gas turbine engine components, including spacers. These forces can adversely affect gas turbine engine performance and reliability, particularly when they are either unpredictable or difficult to control. Reinforcing a spacer with a fiber may allow a lower system weight, more compact or configurable internal packaging or a high degree of reinforcement.

    Abstract translation: 燃气涡轮发动机的间隔件用纤维增强。 纤维可以用基材固化以形成纤维增强复合材料。 当燃气涡轮发动机运行时，旋转产生能够使包括间隔件在内的某些燃气涡轮发动机部件变形，膨胀，收缩或平移的力。 这些力可能不利地影响燃气轮机的性能和可靠性，特别是当它们不可预测或难以控制时。 用纤维增强间隔物可能会降低系统重量，更紧凑或可配置的内部包装或高度的增强。

    Fiber reinforced spacer for a gas turbine engine
    6.
    发明授权
    Fiber reinforced spacer for a gas turbine engine 有权

    公开(公告)号：US10648481B2

    公开(公告)日：2020-05-12

    申请号：US14929701

    申请日：2015-11-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

    IPC: F02C1/00 ,  F04D29/32 ,  F01D5/02 ,  F01D25/28 ,  F02C3/06

    Abstract: A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material. As a gas turbine engine operates, the rotation creates forces which can deform, expand, contract or translate certain gas turbine engine components, including spacers. These forces can adversely affect gas turbine engine performance and reliability, particularly when they are either unpredictable or difficult to control. Reinforcing a spacer with a fiber may allow a lower system weight, more compact or configurable internal packaging or a high degree of reinforcement.

    Reinforced gas turbine engine rotor disk
    7.
    发明授权
    Reinforced gas turbine engine rotor disk 有权

    公开(公告)号：US10370971B2

    公开(公告)日：2019-08-06

    申请号：US14929771

    申请日：2015-11-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

    IPC: F01D5/02 ,  F01D5/06 ,  F01D5/34 ,  F02C3/04

    Abstract: A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.

    COOLED COMPRESSOR
    10.
    发明申请
    COOLED COMPRESSOR 审中-公开
    冷却压缩机

    公开(公告)号：US20170002834A1

    公开(公告)日：2017-01-05

    申请号：US14902373

    申请日：2014-07-10

    Applicant: United Technologies Corporation

    Inventor： Brad Powell ,  Anthony R. Bifulco ,  Paul E. Coderre

    IPC: F04D29/58 ,  F04D27/00 ,  F04D29/32 ,  F04D19/02

    CPC classification number: F04D29/5826 ,  F01D5/082 ,  F01D5/084 ,  F02C7/185 ,  F04B1/2064 ,  F04B1/324 ,  F04D19/02 ,  F04D27/002 ,  F04D29/321 ,  F04D29/5833 ,  F04D29/584 ,  F05B2220/302

    Abstract: An example method of cooling a compressor section of a gas turbine engine includes diverting a flow from a compressor through a heat exchanger, the flow moving from the compressor in a first direction, and moving the flow from the heat exchanger back to the compressor in a second direction. An example spacer for a compressor of a gas turbine engine includes a first side portion, a second side portion spaced apart from the first side portion, and a middle web arranged between the first and second side portions. At least one of the first and second side portions and the middle web include at least one orifice to communicate flow in a direction that is different from a core flowpath flow direction. An example compressor including the spacer is also disclosed.

    Abstract translation: 一种冷却燃气涡轮发动机的压缩机部分的示例性方法包括使来自压缩机的流动通过热交换器转向，该流量从压缩机沿第一方向移动，并且将流体从热交换器移回到压缩机中 第二个方向 用于燃气涡轮发动机的压缩机的示例性间隔件包括第一侧部分，与第一侧部分间隔开的第二侧部以及布置在第一和第二侧部之间的中间腹板。 第一和第二侧部和中间腹板中的至少一个包括至少一个孔，以在不同于芯流路流动方向的方向上传递流。 还公开了包括间隔件的示例性压缩机。

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