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    DOUBLE SNAPPED COVER PLATE FOR ROTOR DISK
    2.
    发明申请
    DOUBLE SNAPPED COVER PLATE FOR ROTOR DISK 审中-公开
    用于转盘的双重安装盖板

    公开(公告)号：US20150369061A1

    公开(公告)日：2015-12-24

    申请号：US14764021

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jonathan Perry Sandoval ,  Raymond S. Hummel ,  Scott D. Virkler

    IPC: F01D5/30 ,  F02C3/04

    CPC classification number: F01D5/3015 ,  F01D5/082 ,  F01D11/001 ,  F02C3/04 ,  F02C7/28 ,  F04D29/321 ,  F05D2260/30 ,  F05D2260/36 ,  Y02T50/676

    Abstract: According to an exemplary embodiment of this disclosure, among other possible things a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor section, a plurality of turbine disks in at least one of the compressor section and the turbine sections, at least one cover plate corresponding to at least one of the turbine disks, each of the cover plates includes, at least two snaps connected via a webbing portion, and a bore region radially inward of the at least two snaps and connected to at least one of the at least two snaps via the webbing portion.

    Abstract translation: 根据本公开的示例性实施例，除了其它可能的情况之外，燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器部分流体连通的涡轮机部分，处于 压缩机部分和涡轮机部分中的至少一个，至少一个与至少一个涡轮盘对应的盖板，每个盖板包括经由织带部分连接的至少两个卡扣和径向向内 所述至少两个卡扣并且经由所述织带部分连接到所述至少两个卡扣中的至少一个卡扣。

    Double snapped cover plate for rotor disk
    3.
    发明授权
    Double snapped cover plate for rotor disk 有权

    公开(公告)号：US10458258B2

    公开(公告)日：2019-10-29

    申请号：US14764021

    申请日：2013-01-30

    Applicant: United Technologies Corporation

    Inventor： Jonathan Perry Sandoval ,  Raymond S. Hummel ,  Scott D. Virkler

    IPC: F01D1/00 ,  F01D5/30 ,  F01D5/08 ,  F04D29/32 ,  F02C3/04 ,  F01D11/00 ,  F02C7/28

    Abstract: According to an exemplary embodiment of this disclosure, among other possible things a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor section, a plurality of turbine disks in at least one of the compressor section and the turbine sections, at least one cover plate corresponding to at least one of the turbine disks, each of the cover plates includes, at least two snaps connected via a webbing portion, and a bore region radially inward of the at least two snaps and connected to at least one of the at least two snaps via the webbing portion.

    Gas turbine engine having a turbine rotor with torque transfer and balance features
    4.
    发明授权
    Gas turbine engine having a turbine rotor with torque transfer and balance features 有权

    公开(公告)号：US10323519B2

    公开(公告)日：2019-06-18

    申请号：US15190494

    申请日：2016-06-23

    Applicant: United Technologies Corporation

    Inventor： Steven D. Porter ,  Julian Partyka ,  Raymond S. Hummel

    IPC: F01D5/10 ,  F01D5/02 ,  F01D11/00 ,  F02C3/04 ,  F02C7/28 ,  F01D5/06 ,  F01D5/08

    Abstract: A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.

    Mini-disk for gas turbine engine
    5.
    发明授权
    Mini-disk for gas turbine engine 有权

    公开(公告)号：US10400603B2

    公开(公告)日：2019-09-03

    申请号：US15190398

    申请日：2016-06-23

    Applicant: United Technologies Corporation

    Inventor： Raymond S. Hummel ,  Julian Partyka

    IPC: F01D5/06 ,  F01D11/00 ,  F01D5/08 ,  F01D5/02 ,  F01D25/08 ,  F04D29/32

    Abstract: Mini-disks of gas turbine engines are provided having an axially extending portion extending axially with respect to an axis of the engine, the axially extending portion configured to engage with a hub arm of a compressor of the engine, a radially extending portion extends radially with respect to the axis, the radially extending portion configured to engage with an attachment of a turbine disk of the gas turbine engine, an intermediate portion extending between the axially extending portion and the radially extending portion, and at least one mini-disk connector configured to engage with a portion of the turbine disk of the gas turbine engine to prevent radial movement of the mini-disk during operation.

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