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    FEATURE TO PROVIDE COOLING FLOW TO DISK
    1.
    发明申请
    FEATURE TO PROVIDE COOLING FLOW TO DISK 审中-公开
    特点提供冷却流量盘

    公开(公告)号：WO2015073112A2

    公开(公告)日：2015-05-21

    申请号：PCT/US2014/056023

    申请日：2014-09-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    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: 除了别的之外，根据本公开的示例性方面的组件包括盘，在盘的第一轴向侧处提供空腔的盖板，包括由下列部件提供的入口的通道： 所述盘和所述盖板中的至少一个中的凹口与所述腔流体连通，并且所述通道从所述入口延伸到设置在所述盘的与所述第一轴向侧相对的第二轴向侧处的出口，所述出口流体连通 入口和通道被配置为提供从腔体到出口的流体流动。

    BLADE FEATURE TO SUPPORT SEGMENTED COVERPLATE
    2.
    发明申请
    BLADE FEATURE TO SUPPORT SEGMENTED COVERPLATE 审中-公开
    刀片特征支持SEGMENTED COVERPLATE

    公开(公告)号：WO2015112226A2

    公开(公告)日：2015-07-30

    申请号：PCT/US2014/064041

    申请日：2014-11-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    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。 刀片安装到盘上并且被配置为围绕轴线旋转。 平台支撑刀片，并且在前缘具有前缘部分和在后缘处的后缘部分。 前边缘部分和后边缘部分中的至少一个包括由内翼片和与内翼片径向向外间隔开的外翼部限定的口部。 至少一个盖板被内翼片保持抵靠盘片。 还公开了一种燃气涡轮发动机。

    ROTOR BLADE WITH L-SHAPED FEATHER SEAL
    5.
    发明申请
    ROTOR BLADE WITH L-SHAPED FEATHER SEAL 审中-公开
    带有L形羽毛密封的转子刀片

    公开(公告)号：WO2014160641A1

    公开(公告)日：2014-10-02

    申请号：PCT/US2014/031581

    申请日：2014-03-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CORCORAN, Christopher ,  CHEROLIS, Anthony P.

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

    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 downstream 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件。 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。 底座包括一个颈部和一个口袋。 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，并且包括基本沿着下游表面延伸的下游腿部。

    GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS
    6.
    发明申请
    GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS 审中-公开
    燃气涡轮发动机，带有密封的密封

    公开(公告)号：WO2015069362A2

    公开(公告)日：2015-05-14

    申请号：PCT/US2014/052032

    申请日：2014-08-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HOUGH, Matthew, Andrew ,  CORCORAN, Christopher ,  BEATTIE, Jeffrey, S.

    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。 多个涡轮叶片安装在盘的周边周围，并且多个密封件布置在涡轮叶片和盘的周边之间。 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。

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