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    Acoustic Panel and Method of Forming
    23.
    发明申请
    Acoustic Panel and Method of Forming 有权
    声学面板和成型方法

    公开(公告)号：US20130206503A1

    公开(公告)日：2013-08-15

    申请号：US13371029

    申请日：2012-02-10

    申请人： Nicholas Joseph Kray ,  Seth Alexander McDonald ,  Benjamin Roby

    发明人： Nicholas Joseph Kray ,  Seth Alexander McDonald ,  Benjamin Roby

    IPC分类号： E04B1/82 ,  B32B38/00

    CPC分类号： F02C7/24 ,  Y02T50/672

    摘要： A disclosed embodiment provides an acoustic panel having a composite laminate panel having a back sheet layer, a face sheet layer, and a core layer disposed therebetween. The core layer has one or more depressions at an interface between the core layer and the face sheet layer, with the face sheet having a generally uniform thickness across the composite laminate panel. A hole extends through the composite laminate panel at the depressions, and a bolt assembly extends through the hole such that it is countersunk.

    摘要翻译： 所公开的实施例提供了一种具有复合层压板的声学面板，所述复合层压板具有背板层，表面层和设置在其间的芯层。 芯层在芯层和面片层之间的界面处具有一个或多个凹陷，其中该面片在复合层压板上具有大致均匀的厚度。 孔在凹部处延伸穿过复合层压板，并且螺栓组件延伸穿过孔，使得其被埋入。

    COMPOSITE ROTOR AND VANE ASSEMBLIES WITH INTEGRAL AIRFOILS
    24.
    发明申请
    COMPOSITE ROTOR AND VANE ASSEMBLIES WITH INTEGRAL AIRFOILS 有权
    复合转子和带集成空气的风扇组件

    公开(公告)号：US20130156594A1

    公开(公告)日：2013-06-20

    申请号：US13331418

    申请日：2011-12-20

    申请人： Nicholas Joseph Kray ,  Christopher Lee McAfee ,  Dong-Jin Shim

    发明人： Nicholas Joseph Kray ,  Christopher Lee McAfee ,  Dong-Jin Shim

    IPC分类号： F01D5/14 ,  B29C70/06

    CPC分类号： F01D5/282 ,  B29B11/16 ,  B29C70/48 ,  B29L2031/08 ,  F01D5/30 ,  F01D5/34 ,  F01D9/042 ,  F05D2300/6034 ,  Y02T50/672

    摘要： A composite gas turbine engine structure includes a retention ring with airfoils mounted on, integral with, and extending radially away from retention ring. Retention ring includes annular composite plies, a circumferentially segmented airfoil ring including airfoil ring segments disposed around one of outer and inner circumferences of retention ring. Airfoil ring segments include annular bases and radially extending clockwise and counter-clockwise airfoil segments at clockwise and counter-clockwise ends of annular base. Composite airfoils include circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments. A flowpath shell circumferentially disposed around segmented airfoil ring traps annular bases between flowpath shell and retention ring. Composite airfoils airfoils extend through slots in flowpath shell. Plies may be wrapped in a single spiral made from a continuous composite tape. Slots may be circumferentially angled. Circumferentially adjacent ones of clockwise and counter-clockwise airfoil segments may be stitched together.

    摘要翻译： 复合燃气涡轮发动机结构包括具有与保持环安装在一体并与径向远离保持环的翼型的保持环。 保持环包括环形复合层，周向分段的翼型环，包括围绕保持环的外周和内周中的一个设置的翼型环段。 翼型环段包括环形基座和在环形基座的顺时针和逆时针端部处的径向延伸的顺时针和逆时针的翼型段。 复合翼型件包括沿周向相邻的顺时针和逆时针翼型段。 围绕分段翼型环周向设置的流路外壳环流体流路外壳和保持环之间的环形基座。 复合翼型翼型件延伸穿过流道外壳中的槽。 层可以包裹在由连续的复合胶带制成的单个螺旋。 槽可以是周向成角度的。 沿顺时针方向和逆时针方向的翼型段可以缝合在一起。

    Airfoils including compliant tip
    29.
    发明授权
    Airfoils including compliant tip 有权
    翼型包括合适的尖端

    公开(公告)号：US09085989B2

    公开(公告)日：2015-07-21

    申请号：US13336001

    申请日：2011-12-23

    申请人： Pranav Dhoj Shah ,  Scott Roger Finn ,  Nicholas Joseph Kray ,  Ian Francis Prentice ,  Dong-Jin Shim ,  Bo Wang

    发明人： Pranav Dhoj Shah ,  Scott Roger Finn ,  Nicholas Joseph Kray ,  Ian Francis Prentice ,  Dong-Jin Shim ,  Bo Wang

    IPC分类号： F01D5/20 ,  F01D21/04

    CPC分类号： F01D5/20 ,  F01D21/045 ,  F05D2300/43 ,  F05D2300/431 ,  F05D2300/432 ,  Y02T50/672 ,  Y02T50/673

    摘要： An airfoil, a fan assembly and an engine include at least one airfoil including a root portion, a body portion and a tip portion. The body portion is configured extending radially outward from the root portion and the tip portion is configured extending radially outward from the root portion and the body portion. The airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil including a compliant tip at the tip portion. The compliant tip extending along at least a portion of the tip portion in a chord-wise direction and a span-wise direction. The compliant tip is configured to provide wave propagation along the tip portion such that critical strain proximate the tip portion and the trailing edge is reduced during a foreign object impact.

    摘要翻译： 翼型件，风扇组件和发动机包括至少一个包括根部，主体部分和顶端部分的翼型件。 主体部分被配置为从根部径向向外延伸，并且尖端部分被构造成从根部部分和主体部分径向向外延伸。 所述翼型件包括在前缘和后缘处连接在一起并在其间延伸的吸力和压力侧。 所述翼型件在尖端部分包括柔性尖端。 柔性尖端沿着顶端部分的至少一部分沿着弦向和跨度方向延伸。 柔性尖端构造成沿着尖端部分提供波传播，使得在异物冲击期间，靠近尖端部分和后缘的临界应变减小。