公开(公告)号：US20090280257A1

公开(公告)日：2009-11-12

申请号：US11012954

申请日：2004-12-14

Applicant: Jay Morrison

Inventor： Jay Morrison

IPC: B05D3/02 ,  C04B35/00

CPC classification number: C04B35/62873 ,  C04B35/803 ,  C04B2235/6028 ,  C04B2235/616

Abstract: A method for forming interphase layers in ceramic matrix composites. The method forms interphase layers in ceramic matrix composites thereby enabling higher matrix densities to be achieved without sacrificing crack deflection and/or toughness. The methods of the present invention involve the use fugitive material-coated fibers. These fibers are then infiltrated with a ceramic matrix slurry. Then, the fugitive material is removed and the resulting material is reinfiltrated with an interphase layer material. The ceramic matrix composite is then fired. Additional steps may be included to densify the ceramic matrix or to increase the strength of the interphase layer. The method is useful for the formation of three dimensional fiber-reinforced ceramic matrix composites envisioned for use in gas turbine components.

Abstract translation: 一种在陶瓷基复合材料中形成相间层的方法。 该方法在陶瓷基体复合材料中形成界面层，从而可以在不牺牲裂纹偏转和/或韧性的情况下实现更高的基体密度。 本发明的方法涉及使用挥发性材料涂覆的纤维。 然后用陶瓷基质浆液渗透这些纤维。 然后，将挥发性材料除去，并将所得材料用相间层材料再渗透。 然后烧制陶瓷基复合材料。 可以包括附加步骤以致密化陶瓷基质或增加界面层的强度。 该方法可用于形成用于燃气轮机部件的三维纤维增强陶瓷基复合材料。

公开(公告)号：US20070108670A1

公开(公告)日：2007-05-17

申请号：US11649061

申请日：2007-01-03

Applicant: Gary Merrill ,  Jay Lane ,  Steven Butner ,  Robert Kreutzer ,  Jay Morrison

Inventor： Gary Merrill ,  Jay Lane ,  Steven Butner ,  Robert Kreutzer ,  Jay Morrison

IPC: C04B33/32 ,  B28B1/00

CPC classification number: C04B38/085 ,  B28B11/041 ,  C04B28/00 ,  C04B28/18 ,  C04B28/34 ,  C04B35/117 ,  C04B35/18 ,  C04B35/803 ,  C04B41/009 ,  C04B41/5092 ,  C04B41/85 ,  C04B2235/3217 ,  C04B2235/3463 ,  C04B2235/5228 ,  C04B2235/528 ,  C04B2235/5436 ,  C04B2235/5445 ,  C04B2235/5472 ,  C04B2235/616 ,  Y10T428/249973 ,  C04B20/0036 ,  C04B20/004 ,  C04B14/303 ,  C04B14/306 ,  C04B14/324 ,  C04B14/328 ,  C04B20/0048 ,  C04B20/0076 ,  C04B38/0061 ,  C04B38/08

Abstract: A composite material (10) formed of a ceramic matrix composite (CMC) material (12) protected by a ceramic insulating material (14). The constituent parts of the insulating material are selected to avoid degradation of the CMC material when the two layers are co-processed. The CMC material is processed to a predetermined state of shrinkage before wet insulating material is applied against the CMC material. The two materials are then co-fired together, with the relative amount of shrinkage between the two materials during the firing step being affected by the amount of pre-shrinkage of the CMC material during the bisque firing step. The shrinkage of the two materials during the co-firing step may be matched to minimize shrinkage stresses, or a predetermined amount of prestress between the materials may be achieved. An aluminum hydroxyl chloride binder material (24) may be used in the insulating material in order to avoid degradation of the fabric (28) of the CMC material during the co-firing step.

Abstract translation: 由陶瓷绝缘材料（14）保护的陶瓷基复合材料（CMC）材料（12）形成的复合材料（10）。 选择绝缘材料的组成部分以避免当两层被共同处理时CMC材料的劣化。 在向CMC材料施加湿绝缘材料之前，将CMC材料加工成预定的收缩状态。 然后将两种材料共烧，在焙烧步骤期间两种材料之间的相对收缩量受到在坯料烧结步骤期间CMC材料的预收缩量的影响。 可以在共烧步骤期间两种材料的收缩率相匹配以最小化收缩应力，或者可以实现材料之间的预定量的预应力。 可以在绝缘材料中使用铝羟基氯化物粘合剂材料（24），以避免在共烧烧步骤期间CMC材料的织物（28）的降解。

公开(公告)号：US20160282086A1

公开(公告)日：2016-09-29

申请号：US15170868

申请日：2016-06-01

Applicant: Jay Morrison

Inventor： Jay Morrison

IPC: F41G1/467

CPC classification number: F41G1/467 ,  F41B5/1492 ,  F41G1/35

Abstract: A multiple laser sight system for an archery bow or the like configured so that the multiple laser systems can be calibrated together and having features such that the user can use one laser system during the day and one laser system during the light. The laser sight is further configured to not interfere with the optional use of conventional sighting pins and the use of evening infrared systems, like the prior art use of night vision goggles.

公开(公告)号：US09377272B2

公开(公告)日：2016-06-28

申请号：US14455445

申请日：2014-08-08

Applicant: Jay Morrison

Inventor： Jay Morrison

IPC: F41G1/467 ,  F41B5/14 ,  F41G1/35

CPC classification number: F41G1/467 ,  F41B5/1492 ,  F41G1/35

Abstract: A multiple laser sight system for an archery bow or the like configured so that the multiple laser systems can be calibrated together and having features such that the user can use one laser system during the day and one laser system during the light. The laser sight is further configured to not interfere with the optional use of conventional sighting pins and the use of evening infrared systems, like the prior art use of night vision goggles.

Abstract translation: 用于射箭弓等的多重激光瞄准系统被配置为使得多个激光系统可以被校准在一起并且具有这样的特征，使得用户可以在白天使用一个激光系统，并且在光线期间使用一个激光系统。 激光瞄准器被进一步构造成不干扰常规瞄准杆的可选使用以及晚上红外系统的使用，如现有技术使用夜视镜。

公开(公告)号：US20060121265A1

公开(公告)日：2006-06-08

申请号：US11002028

申请日：2004-12-02

Applicant: Daniel Thompson ,  Steven Vance ,  Jay Morrison

Inventor： Daniel Thompson ,  Steven Vance ,  Jay Morrison

IPC: B32B18/00 ,  B32B17/12 ,  B32B9/00 ,  B32B19/00

CPC classification number: F04D29/388 ,  F01D5/147 ,  F05D2230/23 ,  F05D2300/601 ,  F05D2300/603 ,  F05D2300/614 ,  Y10T428/249928 ,  Y10T428/249929

Abstract: Embodiments of the invention relate to a robust turbine vane made of stacked airfoil-shaped CMC laminates. Each laminate has an in-plane direction and a through thickness direction substantially normal to the in-plane direction. The laminates have anisotropic strength characteristics in which the in-plane tensile strength is substantially greater than the through thickness tensile strength. Thus, the laminates can provide strength in the direction of high thermal gradients and, thus, withstand the associated high thermal stresses. The laminates are relatively weak in through thickness (interlaminar) tension, but, in operation, relatively low through thickness tensile stresses can be expected. The laminates can be strong in through thickness compression; accordingly, the laminate stack can be held in through thickness compression by one or more fasteners. The CMC material can permit the inclusion of additional features such as cooling passages, ribs, spars, and thermal coatings, without compromising the strength characteristics of the material.

公开(公告)号：US20050167878A1

公开(公告)日：2005-08-04

申请号：US10767012

申请日：2004-01-29

Applicant: Jay Morrison ,  Gary Merrill ,  Steven Vance ,  Michael Burke

Inventor： Jay Morrison ,  Gary Merrill ,  Steven Vance ,  Michael Burke

IPC: B28B7/34 ,  B28B11/08 ,  B28B19/00 ,  B29C33/76 ,  B29C39/02 ,  B29C39/12

CPC classification number: B28B7/342 ,  B28B11/08 ,  B28B19/00 ,  C04B2235/6028 ,  F05D2300/6033 ,  Y10S264/44

Abstract: A method of manufacturing a hybrid structure (100) having a layer of CMC material (28) defining an interior passageway (24) and a layer of ceramic insulating material (18) lining the passageway. The method includes the step of casting the insulating material to a first thickness required for effective casting but in excess of a desired second thickness for use of the hybrid structure. An inner mold (14) defining a net shape desired for the passageway remains in place after the casting step to mechanically support the insulating material during a machining process used to reduce the thickness of the insulating material from the as-cast first thickness to the desired second thickness. The inner mold also provides support as the CMC material is deposited onto the insulating material. The inner mold may include a fugitive material portion (20) to facilitate its removal after the CMC material is formed.

Abstract translation: 一种制造具有限定内部通道（24）的CMC材料层（28）和衬套通道的陶瓷绝缘材料层（18）的混合结构（100）的方法。 该方法包括将绝缘材料浇铸到有效铸造所需的第一厚度但超过所需的第二厚度以用于混合结构的步骤。 限定通道所需的净形状的内模（14）在铸造步骤之后保持就位，以在用于将绝缘材料的厚度从铸造第一厚度减小到期望的机械加工过程期间机械地支撑绝缘材料 第二厚度。 当CMC材料沉积到绝缘材料上时，内模还提供支撑。 内部模具可以包括短暂材料部分（20），以便在形成CMC材料之后便于其移除。

公开(公告)号：US20050022921A1

公开(公告)日：2005-02-03

申请号：US10631277

申请日：2003-07-31

Applicant: Jay Morrison ,  Gary Merrill ,  Thomas Jackson

Inventor： Jay Morrison ,  Gary Merrill ,  Thomas Jackson

IPC: B05B1/00 ,  B32B5/16 ,  C03B29/00 ,  C04B37/00 ,  B32B31/00

CPC classification number: 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

Abstract: 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.

Abstract translation: 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）。

公开(公告)号：US07666475B2

公开(公告)日：2010-02-23

申请号：US11012954

申请日：2004-12-14

Applicant: Jay Morrison

Inventor： Jay Morrison

IPC: C23C16/00

CPC classification number: C04B35/62873 ,  C04B35/803 ,  C04B2235/6028 ,  C04B2235/616

Abstract: A method for forming interphase layers in ceramic matrix composites. The method forms interphase layers in ceramic matrix composites thereby enabling higher matrix densities to be achieved without sacrificing crack deflection and/or toughness. The methods of the present invention involve the use fugitive material-coated fibers. These fibers are then infiltrated with a ceramic matrix slurry. Then, the fugitive material is removed and the resulting material is reinfiltrated with an interphase layer material. The ceramic matrix composite is then fired. Additional steps may be included to densify the ceramic matrix or to increase the strength of the interphase layer. The method is useful for the formation of three dimensional fiber-reinforced ceramic matrix composites envisioned for use in gas turbine components.

Abstract translation: 一种在陶瓷基复合材料中形成相间层的方法。 该方法在陶瓷基体复合材料中形成界面层，从而可以在不牺牲裂纹偏转和/或韧性的情况下实现更高的基体密度。 本发明的方法涉及使用挥发性材料涂覆的纤维。 然后用陶瓷基质浆液渗透这些纤维。 然后，将挥发性材料除去，并将所得材料用相间层材料再渗透。 然后烧制陶瓷基复合材料。 可以包括附加步骤以致密化陶瓷基质或增加界面层的强度。 该方法可用于形成用于燃气轮机部件的三维纤维增强陶瓷基复合材料。

公开(公告)号：US20060121296A1

公开(公告)日：2006-06-08

申请号：US11031796

申请日：2005-01-07

Applicant: Jay Morrison ,  Daniel Thompson ,  Gary Merrill ,  Jay Lane

Inventor： Jay Morrison ,  Daniel Thompson ,  Gary Merrill ,  Jay Lane

IPC: B05D3/02

CPC classification number: F01D5/147 ,  F04D29/388 ,  F05D2230/23 ,  F05D2300/601 ,  F05D2300/603 ,  F05D2300/614

Abstract: A thermal barrier layer (20) is formed by exposing an oxide ceramic material to a thermal regiment to create a surface heat affected zone effective to protect an underlying structural layer (18) of the material. The heat affected surface layer exhibits a lower strength and higher thermal conductivity than the underlying load-carrying material; however, it retains a sufficiently low thermal conductivity to function as an effective thermal barrier coating. Importantly, because the degraded material retains the same composition and thermal expansion characteristics as the underlying material, the thermal barrier layer remains integrally connected in graded fashion with the underlying material without an interface boundary there between. This invention is particularly advantageous when embodied in an apparatus formed of an oxide-oxide ceramic matrix composite (CMC) material wherein reinforcing fibers (24) are anchored in the underlying load-carrying portion and extend into the non-structural thermal barrier portion to provide support and to function as surface crack arrestors. In one embodiment an airfoil (10) is formed of a stacked plurality of CMC plates having such a heat-affected thermal barrier layer formed thereon.

Abstract translation: 通过将氧化物陶瓷材料暴露于热团来形成有效保护材料的下面的结构层（18）的表面热影响区域来形成热障层（20）。 受热影响的表层具有比下面的承载材料更低的强度和更高的热导率; 然而，它保持足够低的热导率以用作有效的热障涂层。 重要的是，由于降解的材料保持与下面的材料相同的组成和热膨胀特性，所以热屏障层保持与下面的材料以分级方式整体连接，而其间没有界面边界。 当本发明体现在由氧化物 - 氧化物陶瓷基质复合材料（CMC）材料形成的装置中时，特别有利的是，其中增强纤维（24）锚固在下面的承载部分并延伸到非结构性热障部分中，以提供 支持和作为表面裂纹器。 在一个实施例中，翼片（10）由在其上形成有这种受热影响的热阻挡层的多个CMC板堆叠形成。

公开(公告)号：US20050238491A1

公开(公告)日：2005-10-27

申请号：US10830384

申请日：2004-04-22

Applicant: Jay Morrison ,  Harry Albrecht ,  Yevgeniy Shteyman ,  Thomas Jackson

Inventor： Jay Morrison ,  Harry Albrecht ,  Yevgeniy Shteyman ,  Thomas Jackson

IPC: B63H1/26 ,  F01D5/18 ,  F01D5/28

CPC classification number: F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F05D2300/603 ,  F05D2300/615 ,  Y10T29/49337 ,  Y10T29/49341

Abstract: 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.

Abstract translation: 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。