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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。

    PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE
    2.
    发明申请
    PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE 审中-公开
    用于气体涡轮发动机转子叶片的平台冷却芯

    公开(公告)号：WO2015057310A2

    公开(公告)日：2015-04-23

    申请号：PCT/US2014/053042

    申请日：2014-08-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

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

    CPC classification number: F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  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: 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，至少部分地在翼型内延伸的第一冷却芯，在平台内部的第二冷却芯 以及在所述平台的配合面和所述第二冷却芯之间延伸的第一冷却孔。

    FEATURE TO PROVIDE COOLING FLOW TO DISK
    7.
    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。

    DIFFUSED PLATFORM COOLING HOLES
    8.
    发明申请
    DIFFUSED PLATFORM COOLING HOLES 审中-公开
    扩散平台冷却孔

    公开(公告)号：WO2015047576A1

    公开(公告)日：2015-04-02

    申请号：PCT/US2014/050977

    申请日：2014-08-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： THORNTON, Lane ,  HOUGH, Matthew Andrew

    IPC: F01D5/18 ,  F01D25/12 ,  F02C7/14 ,  F04D29/58

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/292 ,  F05D2250/324 ,  Y02T50/676

    Abstract: A gas turbine engine component has first and second components each having a platform with an upper surface and a lower surface and with a plurality of side faces extending between the upper and lower surfaces. The platforms are arranged adjacent to one another such that one side face of the platform faces a mating side face of an adjacent platform. At least one cooling hole is formed within the platform and has an inlet to receive a cooling flow and an outlet at least at one of the side faces. The at least one cooling hole increases in size in a direction toward the outlet. A method of cooling a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机部件具有第一和第二部件，每个部件具有一个具有上表面和下表面的平台，并且多个侧面在上表面和下表面之间延伸。 平台彼此相邻布置，使得平台的一个侧面面向相邻平台的配合侧面。 在平台内形成至少一个冷却孔，并且至少在一个侧面具有用于接收冷却流的入口和出口。 至少一个冷却孔在朝向出口的方向上尺寸增大。 还公开了一种冷却燃气涡轮发动机的方法。

    GAS TURBINE ENGINE WITH DISK HAVING PERIPHERY WITH PROTRUSIONS
    9.
    发明申请
    GAS TURBINE ENGINE WITH DISK HAVING PERIPHERY WITH PROTRUSIONS 审中-公开
    燃气轮机发动机与磁盘外围与推动

    公开(公告)号：WO2015038305A2

    公开(公告)日：2015-03-19

    申请号：PCT/US2014/051979

    申请日：2014-08-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F01D5/08 ,  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。 该盘具有沿周向间隔开的叶片安装特征和在叶片安装特征之间沿周向延伸的径向外缘表面。 涡轮叶片在叶片安装特征中沿圆周安装在盘上。 密封件径向布置在靠近径向外边缘表面的盘的外部，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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