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    Ceramic matrix composite airfoil trailing edge arrangement
    1.
    发明授权
    Ceramic matrix composite airfoil trailing edge arrangement 有权
    陶瓷基复合翼面后缘布置

    公开(公告)号：US07066717B2

    公开(公告)日：2006-06-27

    申请号：US10830384

    申请日：2004-04-22

    申请人： Jay A. Morrison ,  Harry A. Albrecht ,  Yevgeniy Shteyman ,  Thomas Barrett Jackson

    发明人： Jay A. Morrison ,  Harry A. Albrecht ,  Yevgeniy Shteyman ,  Thomas Barrett Jackson

    IPC分类号： F03D3/02

    CPC分类号： F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F05D2300/603 ,  F05D2300/615 ,  Y10T29/49337 ,  Y10T29/49341

    摘要： An airfoil (30) having a continuous layer of ceramic matrix composite (CMC) material (34) extending from a suction side (33) to a pressure side (35) around a trailing edge portion (31). The CMC material includes an inner wrap (36) extending around an inner trailing edge portion (38) and an outer wrap (40) extending around an outer trailing edge portion (42). A filler material (44) is disposed between the inner and outer wraps to substantially eliminate voids in the trailing edge portion. The filler material may be pre-processed to an intermediate stage and used as a mandrel for forming the outer trailing edge portion, and then co-processed with the inner and outer wraps to a final form. The filler material may be pre-processed to include a desired mechanical feature such as a cooling passage (22) or a protrusion (48). The filler material may include an upper layer (77) and a lower layer (78) separated by an intermediate layer (76) that extends to between the inner wrap and the outer wrap along the suction and/or pressure sides.

    摘要翻译： 具有从吸力侧（33）延伸到围绕后缘部分（31）的压力侧（35）的陶瓷基质复合材料（CMC）材料（CMC）的连续层的翼型件30。 CMC材料包括围绕内部后缘部分（38）延伸的内部包裹物（36）和围绕外部后缘部分（42）延伸的外部包裹物（40）。 填充材料（44）设置在内层和外层之间，以基本上消除后缘部分中的空隙。 填充材料可以预处理到中间阶段，并且用作形成外后缘部分的心轴，然后与内包层和外包层共处理成最终形式。 填充材料可以被预处理以包括期望的机械特征，例如冷却通道（22）或突起（48）。 填充材料可以包括上层（77）和由中间层（76）分开的下层（78），中间层（76）沿着吸力和/或压力侧延伸到内包层和外包裹层之间。

    Radomes, aircraft and spacecraft including such radomes, and methods of forming radomes
    2.
    发明授权
    Radomes, aircraft and spacecraft including such radomes, and methods of forming radomes 有权
    包括这种天线罩的雷达，飞机和航天器，以及形成天线罩的方法

    公开(公告)号：US08130167B2

    公开(公告)日：2012-03-06

    申请号：US12422075

    申请日：2009-04-10

    申请人： John R. Glabe ,  Andrew B. MacFarland ,  Paul C. Kuhl ,  Thomas Barrett Jackson

    发明人： John R. Glabe ,  Andrew B. MacFarland ,  Paul C. Kuhl ,  Thomas Barrett Jackson

    IPC分类号： H01Q1/42 ,  H01Q1/28

    CPC分类号： H01Q1/42

    摘要： Radomes include an outer wall having a first average thickness and an inner wall having a second average thickness that is different from the first average thickness. At least a major portion of the inner wall is separated from at least a major portion of the outer wall by a space therebetween. The outer wall may comprise a layer of ceramic matrix composite (CMC) material. Aircraft and spacecraft include such radomes. Methods of forming radomes include forming an outer wall having a first average thickness, forming an inner wall having a different second average thickness, and coupling together the inner wall and the outer wall in such a manner as to provide a space between at least a major portion of the outer wall and at least a major portion of the inner wall.

    摘要翻译： 放射线体包括具有第一平均厚度的外壁和具有不同于第一平均厚度的第二平均厚度的内壁。 内壁的至少大部分与外壁的至少大部分隔开一段间隔。 外壁可以包括一层陶瓷基复合材料（CMC）材料。 飞机和航天器包括这样的天线罩。 形成天线罩的方法包括形成具有第一平均厚度的外壁，形成具有不同第二平均厚度的内壁，并且以这样的方式将内壁和外壁联接在一起，以便在至少一个主要 外壁的一部分和内壁的至少大部分。

    RADOMES, AIRCRAFT AND SPACECRAFT INCLUDING SUCH RADOMES, AND METHODS OF FORMING RADOMES
    3.
    发明申请
    RADOMES, AIRCRAFT AND SPACECRAFT INCLUDING SUCH RADOMES, AND METHODS OF FORMING RADOMES 有权
    RADOMES，飞机和包括这种雷达的空间，以及形成RADOMES的方法

    公开(公告)号：US20110050516A1

    公开(公告)日：2011-03-03

    申请号：US12422075

    申请日：2009-04-10

    申请人： John R. Glabe ,  Andrew B. MacFarland ,  Paul C. Kuhl ,  Thomas Barrett Jackson

    发明人： John R. Glabe ,  Andrew B. MacFarland ,  Paul C. Kuhl ,  Thomas Barrett Jackson

    IPC分类号： H01Q1/28 ,  H01Q1/42 ,  B29C65/00

    CPC分类号： H01Q1/42

    摘要： Radomes include an outer wall having a first average thickness and an inner wall having a second average thickness that is different from the first average thickness. At least a major portion of the inner wall is separated from at least a major portion of the outer wall by a space therebetween. The outer wall may comprise a layer of ceramic matrix composite (CMC) material. Aircraft and spacecraft include such radomes. Methods of forming radomes include forming an outer wall having a first average thickness, forming an inner wall having a different second average thickness, and coupling together the inner wall and the outer wall in such a manner as to provide a space between at least a major portion of the outer wall and at least a major portion of the inner wall.

    摘要翻译： 放射线体包括具有第一平均厚度的外壁和具有不同于第一平均厚度的第二平均厚度的内壁。 内壁的至少大部分与外壁的至少大部分隔开一段间隔。 外壁可以包括一层陶瓷基复合材料（CMC）材料。 飞机和航天器包括这样的天线罩。 形成天线罩的方法包括形成具有第一平均厚度的外壁，形成具有不同第二平均厚度的内壁，并且以这样的方式将内壁和外壁联接在一起，以便在至少一个主要 外壁的一部分和内壁的至少大部分。

    Bond enhancement for thermally insulated ceramic matrix composite materials
    5.
    发明授权
    Bond enhancement for thermally insulated ceramic matrix composite materials 有权
    绝缘陶瓷基复合材料的粘结强化

    公开(公告)号：US06984277B2

    公开(公告)日：2006-01-10

    申请号：US10631277

    申请日：2003-07-31

    申请人： Jay Alan Morrison ,  Gary Brian Merrill ,  Thomas Barrett Jackson

    发明人： Jay Alan Morrison ,  Gary Brian Merrill ,  Thomas Barrett Jackson

    IPC分类号： B32B31/10 ,  B32B31/12

    CPC分类号： C04B37/005 ,  B32B2315/02 ,  C04B2235/5224 ,  C04B2235/5228 ,  C04B2235/5236 ,  C04B2235/528 ,  C04B2237/062 ,  C04B2237/064 ,  C04B2237/068 ,  C04B2237/34 ,  C04B2237/36 ,  C04B2237/38 ,  C04B2237/592 ,  C04B2237/66 ,  Y10T428/25

    摘要： A composite structure (62) having a bond enhancement member (76) extending across a bond joint (86) between a ceramic matrix composite (CMC) material (80) and a ceramic insulation material (82), and a method of fabricating such a structure. The bond enhancement member may extend completely through the CMC material to be partially embedded in a core material (84) bonded to the CMC material on an opposed side from the insulation material. A mold (26) formed of a fugitive material having particles (18) of a bond enhancement material may be used to form the CMC material. A two-piece mold (38, 46) may be used to drive a bond enhancement member partially into the CMC material. A compressible material (56) containing the bond enhancement member may be compressed between a hard tool (60) and the CMC material to drive a bond enhancement member partially into the CMC material. A surface (98) of a ceramic insulation material (92) having a bond enhancement member (96) extending therefrom may be used as a mold for laying up a CMC material.

    摘要翻译： 具有穿过陶瓷基体复合材料（CMC）材料（80）和陶瓷绝缘材料（82）之间的接合接头（86）延伸的结合强化构件（76）的复合结构（62），以及制造这种 结构体。 粘结增强构件可以完全延伸穿过CMC材料，以部分地嵌入在与绝缘材料相对的一侧上结合到CMC材料的芯材料（84）中。 由具有粘结增强材料的颗粒（18）的缓冲材料形成的模具（26）可用于形成CMC材料。 可以使用两件式模具（38,46）来将粘结增强部件部分地驱动到CMC材料中。 含有粘结增强部件的可压缩材料（56）可以在硬质工具（60）和CMC材料之间被压缩，以将粘合增强部件部分地驱动到CMC材料中。 陶瓷绝缘材料（92）的表面（98）可以用作用于堆放CMC材料的模具，所述陶瓷绝缘材料（92）的表面（98）具有从其延伸的粘结增强部件（96）。