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    TURBINE BLADE DAMPER SEAL
    1.
    发明申请
    TURBINE BLADE DAMPER SEAL 审中-公开
    涡轮叶片阻尼器密封

    公开(公告)号：WO2013154657A3

    公开(公告)日：2013-12-05

    申请号：PCT/US2013023132

    申请日：2013-01-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER DANIEL A ,  LANA KYLE CHARLES ,  SANDOVAL JONATHAN PERRY ,  VIRKLER SCOTT DANIEL ,  TARASKEVICH JAIMIE ,  OTERO EDWIN

    IPC: F01D5/26

    CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

    Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

    Abstract translation: 根据本公开的示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮机叶片的空腔中的阻尼器密封件包括中心主体部分，其具有第一端部区域，相对的第二端部 区域和宽度。 阻尼器密封件还包括从中心主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突片，其限定第一扩大部分，第一扩大部分具有大于 中心主体部分和从中心主体部分的相对的第二端部区域延伸的第二部分。

    TURBINE MINIDISK BUMPER FOR GAS TURBINE ENGINE
    4.
    发明公开
    TURBINE MINIDISK BUMPER FOR GAS TURBINE ENGINE 审中-公开
    涡轮MINI DISC减震器是否燃气涡轮发动机

    公开(公告)号：EP2986824A4

    公开(公告)日：2016-12-21

    申请号：EP14784968

    申请日：2014-04-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SANDOVAL JONATHAN PERRY

    IPC: F01D5/06 ,  F01D5/02 ,  F01D11/00 ,  F02C7/28

    CPC classification number: F02C3/04 ,  F01D5/02 ,  F01D5/066 ,  Y02T50/671

    Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

    TURBINE BLADE DAMPER SEAL
    5.
    发明公开
    TURBINE BLADE DAMPER SEAL 审中-公开
    DÄMPFUNGSDICHTUNGFÜREINE TURBINENSCHAUFEL

    公开(公告)号：EP2836682A4

    公开(公告)日：2016-06-01

    申请号：EP13775907

    申请日：2013-01-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER DANIEL A ,  LANA KYLE CHARLES ,  SANDOVAL JONATHAN PERRY ,  VIRKLER SCOTT DANIEL ,  TARASKEVICH JAIMIE ,  OTERO EDWIN

    IPC: F01D5/26 ,  F01D5/22 ,  F01D5/30 ,  F01D11/00

    CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

    Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

    Abstract translation: 根据本公开的示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮叶片的空腔中的阻尼器密封件包括中心主体部分，其具有第一端部区域，相对的第二端部 区域和宽度。 阻尼器密封件还包括从中心主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突出部，其限定第一扩大部分，第一扩大部分具有大于 中心主体部分和从中心主体部分的相对的第二端部区域延伸的第二部分。

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