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    Blade outer air seal system for controlled tip clearance
    1.
    发明授权
    Blade outer air seal system for controlled tip clearance 有权
    叶片外部空气密封系统，用于控制尖端间隙

    公开(公告)号：US09447696B2

    公开(公告)日：2016-09-20

    申请号：US13727798

    申请日：2012-12-27

    Applicant: Michael G. McCaffrey ,  Brandon T. Rouse ,  Thomas Almy ,  Igor S. Garcia ,  John R. Farris ,  Mark Borja

    Inventor： Michael G. McCaffrey ,  Brandon T. Rouse ,  Thomas Almy ,  Igor S. Garcia ,  John R. Farris ,  Mark Borja

    IPC: F01D11/18

    CPC classification number: F01D11/18 ,  F05D2240/11 ,  F05D2300/50212 ,  Y02T50/671

    Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion.

    Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封系统包括由具有第一热膨胀系数的第一材料制成的多个环形载体。 多个密封段分别承载在多个环形载体上。 在多个环形载体中承载环构件。 环构件由与组成中的第一材料不同的第二材料制成。 第二材料具有第二热膨胀系数，使得第一热膨胀系数为第二热膨胀系数的75-175％。

    Assembled blade platform
    2.
    发明授权
    Assembled blade platform 有权
    组装刀片平台

    公开(公告)号：US09376916B2

    公开(公告)日：2016-06-28

    申请号：US13488968

    申请日：2012-06-05

    Applicant: Michael G. McCaffrey ,  Gregory H. Hasko ,  Michael G. Abbott

    Inventor： Michael G. McCaffrey ,  Gregory H. Hasko ,  Michael G. Abbott

    IPC: F01D5/14

    CPC classification number: F01D5/147 ,  C04B37/001 ,  C04B2237/365 ,  C04B2237/38 ,  C04B2237/61 ,  C04B2237/84 ,  Y10T29/49336

    Abstract: A method of making a platform of a blade includes the steps of creating two platform sections by solidifying a material with a fabric in a mold and positioning a band of fabric around the two platform sections to retain an airfoil and define a blade. The method further includes the step of bonding the two platform sections together by solidifying the material to define a platform of a solid material. The platform is not bonded to the airfoil.

    Abstract translation: 制造刀片平台的方法包括以下步骤：通过将模具中的织物固化在模具中并将织物带围绕两个平台部分定位以保持翼型件并限定刀片来创建两个平台部分。 该方法还包括通过固化材料以限定固体材料的平台将两个平台部分结合在一起的步骤。 该平台不与翼型结合。

    Turbine Rotor Non-Metallic Blade Attachment
    5.
    发明申请
    Turbine Rotor Non-Metallic Blade Attachment 有权
    涡轮转子非金属刀片附件

    公开(公告)号：US20130022469A1

    公开(公告)日：2013-01-24

    申请号：US13184736

    申请日：2011-07-18

    Applicant: Michael G. McCaffrey

    Inventor： Michael G. McCaffrey

    IPC: F01D5/30

    CPC classification number: F01D5/3007 ,  F01D5/284 ,  F01D5/3084 ,  F05D2230/22 ,  F05D2300/6033

    Abstract: In an engine disk and blade combination, the metallic disk has a plurality of first blade attachment slots and a plurality of second blade attachment slots circumferentially interspersed with each other. There is a circumferential array of a plurality of first blades. Each first blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said first attachment slots. There is a circumferential array of second blades. Each second blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said second slots. The first blades and second blades are non-metallic. The first blades are radially longer than the second blades. The first slots are radially deeper than the second slots.

    Abstract translation: 在发动机盘和刀片组合中，金属盘具有多个第一刀片附接槽和多个第二刀片附接槽，其周向地彼此散布。 存在多个第一叶片的圆周阵列。 每个第一叶片具有翼型件和附接根部。 附件根分别接收在相关联的所述第一附接槽中。 有第二个叶片的圆周阵列。 每个第二叶片具有翼型件和附接根部。 附着根分别接收在相关联的所述第二槽中。 第一个叶片和第二个叶片是非金属的。 第一叶片比第二叶片径向长。 第一槽比第二槽径向更深。

    PLATFORMLESS TURBINE BLADE
    8.
    发明申请
    PLATFORMLESS TURBINE BLADE 有权
    平板式涡轮叶片

    公开(公告)号：US20090257875A1

    公开(公告)日：2009-10-15

    申请号：US12101326

    申请日：2008-04-11

    Applicant: Michael G. McCaffrey ,  Eric A. Hudson

    Inventor： Michael G. McCaffrey ,  Eric A. Hudson

    IPC: F01D5/22 ,  F01D5/14 ,  F01D5/18 ,  F01D5/02

    CPC classification number: F01D5/3015 ,  F01D11/008 ,  F05D2240/80

    Abstract: A turbine blade rotor assembly is disclosed for a gas turbine engine. The assembly includes a rotor having nickel alloy turbine blades secured thereto. Each of the blades includes a root and an airfoil. The roots are supported by the rotor. A ceramic matrix composite platform separate from the turbine blades is supported between each pair of the turbine blades adjacent to the airfoils. In another example, the airfoil includes a perimeter. A shroud having an aperture receives the airfoil with a single shroud substantially surrounding the airfoil at the perimeter. In one example, the turbine blade includes high and low pressure sides opposite one another that extend from a tip to a root. The airfoil is free from any protrusions extending from the high and low pressure sides on a portion of the blade axially outward from the root.

    Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮叶片转子组件。 组件包括具有固定在其上的镍合金涡轮叶片的转子。 每个叶片包括根部和翼型件。 根部由转子支撑。 与涡轮机叶片分离的陶瓷基体复合平台被支撑在与翼型件相邻的每对涡轮机叶片之间。 在另一示例中，翼型件包括周边。 具有孔径的护罩接收具有在周边基本上围绕翼型件的单个护罩的翼型件。 在一个示例中，涡轮机叶片包括从尖端延伸到根部的彼此相对的高压和低压侧。 叶片从根部的轴向向外的叶片的一部分上的高压侧和低压侧延伸的任何突起都没有。

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