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    TURBINE BLADE AND DAMPER RETENTION
    11.
    发明公开
    TURBINE BLADE AND DAMPER RETENTION 审中-公开
    涡轮叶片和冲击RETENTION

    公开(公告)号：EP2971555A4

    公开(公告)日：2017-02-01

    申请号：EP14773520

    申请日：2014-03-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUGH MATTHEW ANDREW ,  RAPP BRANDON M

    IPC: F01D5/26 ,  F01D5/12 ,  F02C7/00

    CPC classification number: F01D5/10 ,  F01D5/26 ,  F01D5/3007 ,  F01D11/006 ,  F05D2260/96 ,  Y10T29/49323

    Abstract: A gas turbine engine rotor assembly has a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall.

    PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE
    15.
    发明公开
    PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE 审中-公开
    PLATTFORMKÜHLUNGSKERNFÜREINE ROTORSCHAUFEL EINES GASTURBINENMOTORS

    公开(公告)号：EP3047105A4

    公开(公告)日：2017-04-26

    申请号：EP14853976

    申请日：2014-08-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUGH MATTHEW ANDREW ,  BEATTIE JEFFREY S

    IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18

    CPC classification number: F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/2212

    Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.

    Abstract translation: 除了别的之外，根据本公开的示例性方面的转子叶片包括平台，从平台延伸的翼型件，至少部分地在翼型件内部延伸的第一冷却芯件，平台内的第二冷却芯件 以及在平台的配合面和第二冷却芯之间延伸的第一冷却孔。

    GAS TURBINE ENGINE WITH DISK HAVING PERIPHERY WITH PROTRUSIONS
    17.
    发明公开
    GAS TURBINE ENGINE WITH DISK HAVING PERIPHERY WITH PROTRUSIONS 审中-公开
    GASTURBINENMOTOR MIT平板麻醉师PERIPHERIE OHNEVORSPRÜNGE

    公开(公告)号：EP3047102A4

    公开(公告)日：2016-11-16

    申请号：EP14843390

    申请日：2014-08-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUGH MATTHEW ANDREW ,  BEATTIE JEFFREY S

    IPC: F01D5/08 ,  F01D5/30 ,  F01D11/00 ,  F01D11/02 ,  F01D25/12 ,  F02C7/18

    CPC classification number: F01D11/006 ,  F01D5/081 ,  F01D5/3015 ,  F01D11/003 ,  F01D11/005 ,  F01D11/008 ,  F01D11/02 ,  F01D25/12 ,  F05D2240/127 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/2212

    Abstract: A gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features. Turbine blades are mounted circumferentially around the disk in the blade mounting features. Seals are arranged radially outwards of the disk adjacent the radially outer rim surfaces such that there are respective passages between the seals and the radially outer rim surfaces. The radially outer rim surfaces include radially-extending protrusions that extend into the respective passages.

    Abstract translation: 燃气涡轮发动机包括具有可围绕轴线旋转的盘的涡轮部分。 盘具有周向间隔开的叶片安装特征和在叶片安装特征之间周向延伸的径向外缘表面。 涡轮叶片围绕盘安装在叶片安装特征中。 密封件邻近径向外边缘表面径向向外布置，使得在密封件和径向外边缘表面之间存在相应的通道。 径向外边缘表面包括延伸到相应通道中的径向延伸的突起。

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