Turbine blade root profile
    15.
    发明授权
    Turbine blade root profile 有权
    涡轮叶片根型材

    公开(公告)号:US09546556B2

    公开(公告)日:2017-01-17

    申请号:US13626937

    申请日:2012-09-26

    CPC classification number: F01D5/30 F01D5/18 F01D5/3007

    Abstract: A turbine blade for a gas turbine engine includes an airfoil that extends in a first radial direction from a platform. A root extends from the platform in a second radial direction and has opposing lateral sides that provide a firtree-shaped contour. The contour includes first, second and third lobes on each of the lateral sides and that tapers relative to the radial direction away from the platform. The first, second and third lobes each provide contact surfaces arranged at about 45° relative to the radial direction. A contact plane on each lateral side at an angle of about 11° relative to the radial direction defining a contact point on each of the contact surfaces. The first, second and third lobes each include first, second and third grooves that are substantially aligned with one another along an offset plane spaced a uniform offset distance from the contact plane.

    Abstract translation: 用于燃气涡轮发动机的涡轮机叶片包括从平台沿第一径向方向延伸的翼型件。 根部在第二径向方向上从平台延伸并且具有相对的侧向侧面,该侧面侧面提供保持曲面的轮廓。 轮廓包括在每个侧面上的第一,第二和第三凸角,并且相对于远离平台的径向方向逐渐变细。 第一,第二和第三叶片各自提供相对于径向方向布置成大约45°的接触表面。 在每个侧面上的接触平面相对于径向方向以约11°的角度限定每个接触表面上的接触点。 第一,第二和第三凸耳各自包括第一,第二和第三凹槽,其沿着与接触平面间隔开均匀偏移距离的偏移平面彼此基本对齐。

    FEATURE TO PROVIDE COOLING FLOW TO DISK
    16.
    发明申请
    FEATURE TO PROVIDE COOLING FLOW TO DISK 审中-公开
    特点提供冷却流量到盘

    公开(公告)号:US20160222787A1

    公开(公告)日:2016-08-04

    申请号:US15021060

    申请日:2014-09-17

    Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.

    Abstract translation: 根据本公开的示例性方面的组件包括盘,在盘的第一轴向侧提供空腔的盖板,包括由至少一个中的至少一个中的凹口提供的入口的通道 盘和盖板与空腔流体连通,并且从入口延伸到设置在与第一轴向侧相对的盘的第二轴向侧处的出口的通道,与入口流体连通的出口和配置的通道 以提供从空腔到出口的流体流动。

    Blade feature to support segmented coverplate

    公开(公告)号:US10563525B2

    公开(公告)日:2020-02-18

    申请号:US15038536

    申请日:2014-11-05

    Abstract: A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.

    PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE

    公开(公告)号:US20190316475A1

    公开(公告)日:2019-10-17

    申请号:US16427870

    申请日:2019-05-31

    Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends radially from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform, a first cooling hole that extends circumferentially between a mate face of the platform and the second cooling core, a second cooling hole that extends between a gas path surface of the platform and the second cooling core, the second cooling core radially disposed between the gas path surface and a non-gas path surface, and the second cooling core circumferentially disposed between the first cooling core and the mate face. A method of cooling a blade is also disclosed.

Patent Agency Ranking