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    BLADE FEATURE TO SUPPORT SEGMENTED COVERPLATE
    1.
    发明申请
    BLADE FEATURE TO SUPPORT SEGMENTED COVERPLATE 审中-公开
    刀片功能支持分段的封面

    公开(公告)号：WO2015112226A3

    公开(公告)日：2015-10-08

    申请号：PCT/US2014064041

    申请日：2014-11-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUGH MATTHEW ANDREW ,  CORCORAN CHRISTOPHER ,  BEATTIE JEFFREY S

    IPC: F01D5/14 ,  F01D5/30

    CPC classification number: F01D5/3015 ,  F01D25/005 ,  F05D2220/32 ,  Y02T50/671

    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.

    Abstract translation: 燃气涡轮发动机部件包括具有前缘和后缘的叶片。 刀片安装在光盘上并配置为绕轴旋转。 平台支撑叶片，并具有在前缘处的前缘部分和在后缘处的后缘部分。 前缘部分和后缘部分中的至少一个包括由内翼和与内翼径向向外间隔开的外翼限定的口部。 至少一个盖板通过内翼被保持在盘上。 燃气涡轮发动机也被公开。

    FEATURE TO PROVIDE COOLING FLOW TO DISK
    2.
    发明申请
    FEATURE TO PROVIDE COOLING FLOW TO DISK 审中-公开
    提供冷却流的特点

    公开(公告)号：WO2015073112A3

    公开(公告)日：2015-08-20

    申请号：PCT/US2014056023

    申请日：2014-09-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BEATTIE JEFFREY S ,  HIMES JASON D ,  HOUGH MATTHEW ANDREW ,  CORCORAN CHRISTOPHER

    IPC: F01D5/08 ,  F01D5/18

    CPC classification number: F01D5/081 ,  F01D5/082 ,  F01D5/085 ,  F01D5/12 ,  F01D5/187 ,  F01D5/3007 ,  F01D5/3015 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/20

    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。

    GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS
    3.
    发明申请
    GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS 审中-公开
    具有密封的气体涡轮发动机

    公开(公告)号：WO2015069362A3

    公开(公告)日：2015-07-30

    申请号：PCT/US2014052032

    申请日：2014-08-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUGH MATTHEW ANDREW ,  CORCORAN CHRISTOPHER ,  BEATTIE JEFFREY S

    IPC: F01D11/00 ,  F01D5/18

    CPC classification number: F01D11/006 ,  F01D5/22 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/75 ,  F05D2260/22141

    Abstract: A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.

    Abstract translation: 燃气涡轮发动机包括涡轮部分。 涡轮机部分包括可围绕轴线旋转的盘。 多个涡轮机叶片围绕盘的周边安装，并且多个密封件布置在涡轮机叶片与盘周边之间。 每个密封件相对于轴线包括径向外表面和径向内表面。 径向内表面包括多个突起。

    ROTOR BLADE WITH L-SHAPED FEATHER SEAL
    5.
    发明公开
    ROTOR BLADE WITH L-SHAPED FEATHER SEAL 审中-公开
    ROTORBLATT MIT L-FÖRMIGERFEDERDICHTUNG

    公开(公告)号：EP2978938A4

    公开(公告)日：2016-07-20

    申请号：EP14775995

    申请日：2014-03-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CORCORAN CHRISTOPHER ,  CHEROLIS ANTHONY P

    IPC: F01D11/00 ,  F01D5/14 ,  F01D11/22 ,  F02C7/28

    CPC classification number: F01D11/008 ,  F01D5/02 ,  F01D5/147 ,  F01D11/006 ,  F01D15/12 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2260/97

    Abstract: A turbine engine assembly arranged relative to an axis includes a rotor blade and a feather seal with an L-shaped geometry. The rotor blade includes an airfoil and a base. The airfoil extends axially between an upstream leading edge and a downstream trailing edge, and radially out from the base. The base includes a neck and a pocket. The neck extends axially to a downstream surface. The pocket extends laterally into the neck. The feather seal extends laterally into the pocket, and includes a down stream leg that extends substantially along the downstream surface.

    Abstract translation: 相对于轴线布置的涡轮发动机组件包括转子叶片和具有L形几何形状的羽毛密封。 转子叶片包括翼型件和底座。 翼型件在上游前缘和下游后缘之间轴向延伸，并从底座径向延伸。 底座包括一个脖子和一个口袋。 颈部轴向延伸到下游表面。 口袋横向延伸到颈部。 羽毛密封件横向延伸到袋中，并且包括基本上沿着下游表面延伸的下游腿。

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