专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07247003B2 Stacked lamellate assembly 有权
标题翻译：堆叠层状组件
公开(公告)号：US07247003B2
公开(公告)日：2007-07-24
申请号：US11031797
申请日：2005-01-07
申请人： Michael A. Burke , Jay A. Morrison , Steven James Vance , Daniel G. Thompson , Vijay Parthasarathy , Gary B. Merrill , Douglas Allen Keller
发明人： Michael A. Burke , Jay A. Morrison , Steven James Vance , Daniel G. Thompson , Vijay Parthasarathy , Gary B. Merrill , Douglas Allen Keller
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/284 , F04D29/388 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614
摘要： A stacked ceramic matrix composite lamellate assembly (10) including shear force bearing structures (48) for resisting relative sliding movement between adjacent lamellae. The shear force bearing structures may take the form of a cross-lamellar stitch (50), a shear pin (62), a warp (90) in the lamellae, a tongue (104) and groove (98) structure, or an inter-lamellar sealing member (112), in various embodiments. Each shear force bearing structure secures a subset of the lamellae, with at least one lamella being common between adjacent subsets in order to secure the entire assembly.
摘要翻译：一种层叠的陶瓷基复合材料层状组件（10），其包括用于抵抗相邻薄片之间的相对滑动运动的剪切力轴承结构（48）。剪切力承载结构可以采取跨层状缝合（50），剪切销（62），薄片中的经线（90），舌状物（104）和凹槽（98）结构的形式， - 绝缘密封件（112）。每个剪切力轴承结构确保薄片的一个子集，其中至少一个薄片在相邻子集之间是共同的，以便固定整个组件。

2. 发明授权

US07351364B2 Method of manufacturing a hybrid structure 失效
标题翻译：制造混合结构的方法
公开(公告)号：US07351364B2
公开(公告)日：2008-04-01
申请号：US10767012
申请日：2004-01-29
申请人： Jay A. Morrison , Gary B. Merrill , Steven James Vance , Michael A. Burke
发明人： Jay A. Morrison , Gary B. Merrill , Steven James Vance , Michael A. Burke
IPC分类号： B28B11/00 , B28B5/00 , B29C33/76
CPC分类号： B28B7/342 , B28B11/08 , B28B19/00 , C04B2235/6028 , F05D2300/6033 , Y10S264/44
摘要： 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.
摘要翻译：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。

3. 发明授权

US07311790B2 Hybrid structure using ceramic tiles and method of manufacture 有权
标题翻译：使用陶瓷砖的混合结构及其制造方法
公开(公告)号：US07311790B2
公开(公告)日：2007-12-25
申请号：US10767013
申请日：2004-01-29
申请人： Jay A. Morrison , Gary B. Merrill , Michael A. Burke , Jay Edgar Lane , Steven James Vance
发明人： Jay A. Morrison , Gary B. Merrill , Michael A. Burke , Jay Edgar Lane , Steven James Vance
IPC分类号： B32B37/06 , B32B37/14 , B32B38/00 , B32B38/10 , C03B29/00
CPC分类号： B28B19/0053 , B28B21/42 , F05D2300/6033 , F23R3/007
摘要： A hybrid structure (50) and method of manufacturing the same including a structural ceramic matrix composite (CMC) material (42) coated with a layer of ceramic insulating tiles (24). Individual ceramic tiles are attached to a surface (22) of a mold (20). The exterior surface (32) of the tiles may be subjected to a mechanical process such as machining with the mold in place to provide mechanical support for the tiles. A layer of CMC material is then applied to bond the tiles and the CMC material together into a hybrid structure. The mold may include a fugitive material portion (26) to facilitate removal of the mold when the hybrid structure has a complex shape. Tiles located in different regions of the structure may have different compositions and/or dimensions. The gaps between adjacent tiles may be filled from the outside before the CMC material is applied or from the inside after the mold is removed.
摘要翻译：一种混合结构（50）及其制造方法，包括涂覆有陶瓷绝缘砖（24）层的结构陶瓷基复合材料（CMC）材料（42）。单个陶瓷砖附接到模具（20）的表面（22）。瓦片的外表面（32）可以经受机械加工，例如用模具进行机械加工，以为瓦片提供机械支撑。然后施加一层CMC材料以将瓷砖和CMC材料结合在一起成为混合结构。当混合结构具有复杂的形状时，模具可以包括短片材料部分（26），以便于去除模具。位于结构的不同区域的瓷砖可以具有不同的组成和/或尺寸。相邻瓦片之间的间隙可以在CMC材料施加之前从外部填充，或者在模具移除之后从内部填充。

4. 发明授权

US07291407B2 Ceramic material having ceramic matrix composite backing and method of manufacturing 有权
标题翻译：陶瓷材料具有陶瓷基复合背衬及其制造方法
公开(公告)号：US07291407B2
公开(公告)日：2007-11-06
申请号：US10654751
申请日：2003-09-04
申请人： Gary B. Merrill , Michael A. Burke , Stefan Hoffmann , Jay A. Morrison , Marc Tertilt , Daniel Hofmann , Daniel G. Thompson
发明人： Gary B. Merrill , Michael A. Burke , Stefan Hoffmann , Jay A. Morrison , Marc Tertilt , Daniel Hofmann , Daniel G. Thompson
IPC分类号： B32B19/00
CPC分类号： F23R3/007 , B32B2315/02 , C04B35/10 , C04B35/185 , C04B35/6316 , C04B35/803 , C04B37/005 , C04B2235/3418 , C04B2235/5228 , C04B2235/94 , C04B2235/96 , C04B2237/062 , C04B2237/064 , C04B2237/10 , C04B2237/38 , F23M2900/05004 , Y02T50/67
摘要： An article comprising a ceramic material having a ceramic matrix composite backing adapted for use in a gas turbine engine is provided. The article comprises a structural ceramic material having a hot side facing toward a high temperature environment and a cold side facing away from the high temperature environment; and a ceramic matrix composite composition having a strength greater than the strength of the ceramic material attached to the back of the cold side of the ceramic material, whereby crack initiation and propagation are inhibited by the ceramic matrix composition to a greater degree than by the ceramic material.
摘要翻译：提供了一种包括具有适用于燃气涡轮发动机的陶瓷基体复合衬底的陶瓷材料的制品。该制品包括具有面向高温环境的热侧和远离高温环境的冷侧的结构陶瓷材料; 陶瓷基复合材料组合物的强度大于陶瓷材料的冷侧背面附着的陶瓷材料的强度，由此陶瓷基体组合物比陶瓷基体组合物更大程度地抑制裂纹的产生和扩展材料。

5. 发明申请

US20100251721A1 Stacked laminate gas turbine component 有权
标题翻译：叠层式燃气轮机组件
公开(公告)号：US20100251721A1
公开(公告)日：2010-10-07
申请号：US11784154
申请日：2007-04-05
申请人： Jay A. Morrison , Gary B. Merrill , Daniel George Thompson , Steven James Vance
发明人： Jay A. Morrison , Gary B. Merrill , Daniel George Thompson , Steven James Vance
IPC分类号： F02C1/00 , F01D11/08 , F01D5/14 , B32B38/10
CPC分类号： F01D5/147 , F01D5/282 , F05D2300/603
摘要： A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material.
摘要翻译：提供了可用作一种或多种金属部件的替代物的用于涡轮发动机的堆叠层叠部件。堆叠的层叠部件可以具有通过堆叠和层压层以形成沿着热气体路径的径向内表面的过程形成的主体。这些层可以基本上垂直于径向内表面。这些层可以是至少第一材料的第一层和第二材料的第二层。至少第一种材料是陶瓷基复合材料。第二材料可以具有比第一材料更高的导热性或更高的蠕变强度。

6. 发明授权

US08528339B2 Stacked laminate gas turbine component 有权
标题翻译：叠层式燃气轮机组件
公开(公告)号：US08528339B2
公开(公告)日：2013-09-10
申请号：US11784154
申请日：2007-04-05
申请人： Jay A. Morrison , Gary B. Merrill , Daniel George Thompson , Steven James Vance
发明人： Jay A. Morrison , Gary B. Merrill , Daniel George Thompson , Steven James Vance
IPC分类号： F04D29/54
CPC分类号： F01D5/147 , F01D5/282 , F05D2300/603
摘要： A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material.
摘要翻译：提供了可用作一种或多种金属部件的替代物的用于涡轮发动机的堆叠层叠部件。堆叠的层叠部件可以具有通过堆叠和层压层以形成沿着热气体路径的径向内表面的过程形成的主体。这些层可以基本上垂直于径向内表面。这些层可以是至少第一材料的第一层和第二材料的第二层。至少第一种材料是陶瓷基复合材料。第二材料可以具有比第一材料更高的导热性或更高的蠕变强度。

7. 发明申请

US20100119777A1 Ceramic matrix composite surfaces with open features for improved bonding to coatings 审中-公开
标题翻译：具有开放特征的陶瓷基体复合材料表面，用于改善与涂层的结合
公开(公告)号：US20100119777A1
公开(公告)日：2010-05-13
申请号：US11600709
申请日：2006-11-16
申请人： Gary B. Merrill , Jay A. Morrison , Jay E. Lane , Steven James Vance
发明人： Gary B. Merrill , Jay A. Morrison , Jay E. Lane , Steven James Vance
IPC分类号： B32B3/30 , B05D3/12
CPC分类号： C04B41/5027 , B32B5/12 , B32B5/26 , B32B5/30 , B32B2260/025 , B32B2264/107 , B32B2307/304 , C04B41/009 , C04B41/87 , D03D15/0016 , D03D15/02 , D03D25/005 , D04C1/06 , D10B2505/02 , F05C2253/02 , F05C2253/04 , F05C2253/12 , Y10T428/24479 , C04B20/004 , C04B35/80
摘要： A method to form an improved hybrid ceramic matrix composite structure comprises providing a ceramic matrix composite (CMC) with open features at a surface and applying a thermal barrier coating to the surface. The thermal barrier coating is preferably a friable graded insulation coating (FGI) having hollow ceramic spheres. For acceptance of a FGI coating the open features have a center-to-center separation distance in one or more directions that is between about 100 and about 1,000 percent of the diameter of the hollow ceramic spheres in the FGI and a depth that is between about 20 percent and about 200 percent of the diameter of the hollow ceramic spheres in the FGI. The open feature can result from the winding of tows about a mandrel; the lay-up of fabric including a surface fabric having an open weave; or the use of a 3-D weave, or a 3-D braid.
摘要翻译：形成改进的混合陶瓷基质复合结构的方法包括提供在表面上具有开放特征的陶瓷基质复合材料（CMC），并向表面施加热障涂层。隔热涂层优选是具有中空陶瓷球的易碎梯度绝缘涂层（FGI）。为了接受FGI涂层，开口特征在一个或多个方向上具有中心到中心的间隔距离，其在FGI中的中空陶瓷球的直径的大约100％到大约1000％之间，并且在大约在FGI中的中空陶瓷球的直径的20％和约200％。打开的特征可以由围绕心轴缠绕的丝束产生; 包括具有开放编织物的表面织物的织物铺设; 或使用3-D编织物或3-D编织物。

8. 发明授权

US07258530B2 CMC component and method of fabrication 有权
标题翻译： CMC组件和制造方法
公开(公告)号：US07258530B2
公开(公告)日：2007-08-21
申请号：US11040464
申请日：2005-01-21
申请人： Jay A. Morrison , Gary B. Merrill , Steven James Vance , Harry A. Albrecht , Yevgeniy Shteyman
发明人： Jay A. Morrison , Gary B. Merrill , Steven James Vance , Harry A. Albrecht , Yevgeniy Shteyman
IPC分类号： F01D5/14
CPC分类号： F01D5/284 , F01D5/147 , F01D5/282 , Y10T29/49337 , Y10T29/49339
摘要： An airfoil (44) formed of a plurality of pre-fired structural CMC panels (46, 48, 50, 52). Each panel is formed to have an open shape having opposed ends (54) that are free to move during the drying, curing and/or firing of the CMC material in order to minimize interlaminar stresses caused by anisotropic sintering shrinkage. The panels are at least partially pre-shrunk prior to being joined together to form the desired structure, such as an airfoil (42) for a gas turbine engine. The panels may be joined together using a backing member (30), using flanged ends (54) and a clamp (56), and/or with a bond material (36), for example.
摘要翻译：由多个预烧结构的CMC板（46,48,50,52）形成的翼型件（44）。每个板形成为具有相对端（54）的开放形状，其在CMC材料的干燥，固化和/或烧制期间自由移动，以便最小化由各向异性烧结收缩引起的层间应力。在连接在一起以形成期望的结构之前，板至少部分地预收缩，例如用于燃气涡轮发动机的翼型件（42）。例如，使用凸缘端部（54）和夹具（56）和/或与粘合材料（36）一起使用背衬构件（30）将面板连接在一起。

9. 发明授权

US07402347B2 In-situ formed thermal barrier coating for a ceramic component 有权
标题翻译：用于陶瓷部件的原位形成的热障涂层
公开(公告)号：US07402347B2
公开(公告)日：2008-07-22
申请号：US11031796
申请日：2005-01-07
申请人： Jay A. Morrison , Daniel G. Thompson , Gary B. Merrill , Jay Edgar Lane
发明人： Jay A. Morrison , Daniel G. Thompson , Gary B. Merrill , Jay Edgar Lane
IPC分类号： B64C11/16 , B64C27/46 , F01D5/14 , B63H27/46
CPC分类号： F01D5/147 , F04D29/388 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614
摘要： 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.
摘要翻译：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。

10. 发明授权

US06514046B1 Ceramic composite vane with metallic substructure 有权
标题翻译：陶瓷复合叶片与金属子结构
公开(公告)号：US06514046B1
公开(公告)日：2003-02-04
申请号：US09677044
申请日：2000-09-29
申请人： Jay A. Morrison , Gary B. Merrill , Jay E. Lane , Christian X. Campbell , Daniel G. Thompson , Eric V. Carelli , Christine Taut
发明人： Jay A. Morrison , Gary B. Merrill , Jay E. Lane , Christian X. Campbell , Daniel G. Thompson , Eric V. Carelli , Christine Taut
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/282 , F01D5/284 , F01D9/02 , F05D2260/201 , F05D2300/603 , F05D2300/611 , F05D2300/612
摘要： A vane assembly for a turbine assembly includes an inner endcap, an outer endcap, and a body. The body includes a metallic core assembly, a ceramic shell assembly and a support assembly. The metallic core assembly is coupled to the inner and outer endcaps and bears most of the mechanical loads, including aerodynamic loads. The ceramic shell bears substantially all of the thermal stress placed on the vane assembly. The support assembly is disposed between the metallic core assembly and said ceramic shell assembly and is coupled to the metallic core assembly.
摘要翻译：用于涡轮组件的叶片组件包括内端盖，外端盖和主体。主体包括金属芯组件，陶瓷壳组件和支撑组件。金属芯组件联接到内外端盖和承载大部分机械负载，包括空气动力学负载。陶瓷壳承受放置在叶片组件上的基本上所有的热应力。支撑组件设置在金属芯组件和所述陶瓷壳组件之间并且联接到金属芯组件。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式