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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。

    TURBINE BLADE ROOT WITH MICROCIRCUIT COOLING PASSAGES
    2.
    发明申请
    TURBINE BLADE ROOT WITH MICROCIRCUIT COOLING PASSAGES 审中-公开
    涡轮叶片带微型冷却通道

    公开(公告)号：WO2014025440A2

    公开(公告)日：2014-02-13

    申请号：PCT/US2013/041776

    申请日：2013-05-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： BEATTIE, Jeffrey S. ,  JACQUES, Jeffrey Michael ,  PIGGUSH, Justin D.

    CPC classification number: F01D5/187 ,  B22C9/04 ,  B22C9/103 ,  F05D2230/211 ,  F05D2260/204 ,  Y02T50/676 ,  Y10T29/49316

    Abstract: A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.

    Abstract translation: 一种制造翼型的方法包括以下步骤：制造第一芯，其包括限定完成的翼型件的第一多个通道的第一多个肋，并且制造为第二芯，该第二芯包括限定第二多个通路的第二多个肋 完成机翼。 第二多个肋包括多个支座。 所述多个支座在所述第一多个肋与所述第二多个肋之间设置间隔，以限定所述第一多个通道与所述完整翼型的所述第二多个通道之间的间隔。 然后将翼型件围绕芯组件成型。 一旦完成，移除芯组件以提供具有期望的稳定性和结构完整性的并入多个微电路的完整翼型件。

    INSPECTING ONE OR MORE APERTURES OF A COMPONENT USING MOLDABLE MATERIAL
    4.
    发明申请
    INSPECTING ONE OR MORE APERTURES OF A COMPONENT USING MOLDABLE MATERIAL 审中-公开
    使用可塑材料检查组件的一个或多个孔

    公开(公告)号：WO2014134057A1

    公开(公告)日：2014-09-04

    申请号：PCT/US2014/018370

    申请日：2014-02-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： REED, Gordon M. ,  ROMANELLI, James ,  KOONANKEIL, James M. ,  KLINEFELTER, Kevin J. ,  FRITCH, Markus W. ,  HOLLMAN, Kenneth J. ,  BEATTIE, Jeffrey S.

    IPC: G01B11/00 ,  G01M13/00

    CPC classification number: G01B11/00 ,  G01B11/24 ,  G01B21/20 ,  G01M13/00

    Abstract: A method is provided for inspecting at least one aperture of a component with curable material and an inspection system. At least a portion of the curable material is injected into the aperture. The curable material conforms to at least a portion the aperture and subsequently cures and forms a mold of at least a portion of the aperture. The mold is removed from the aperture. At least a portion of a geometry of the mold is compared to at least a portion of a geometry of a reference model for the aperture using the inspection system.

    Abstract translation: 提供了一种用于使用可固化材料和检查系统检查部件的至少一个孔的方法。 至少一部分可固化材料被注入孔中。 可固化材料符合孔的至少一部分并随后固化并形成孔的至少一部分的模具。 将模具从孔中取出。 将模具的几何形状的至少一部分与使用检查系统的孔的参考模型的几何形状的至少一部分进行比较。

    PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE
    8.
    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。

    TURBINE BLADE ROOT PROFILE
    10.
    发明申请
    TURBINE BLADE ROOT PROFILE 审中-公开
    涡轮叶片轮廓

    公开(公告)号：WO2014099082A2

    公开(公告)日：2014-06-26

    申请号：PCT/US2013/061920

    申请日：2013-09-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： BEATTIE, Jeffrey S. ,  JACQUES, Jeffrey Michael

    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准。

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