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1. 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。

2. 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。

3. 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。

4. 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。

5. 发明授权

US07153096B2 Stacked laminate CMC turbine vane 有权
标题翻译：堆叠层压板CMC涡轮叶片
公开(公告)号：US07153096B2
公开(公告)日：2006-12-26
申请号：US11002028
申请日：2004-12-02
申请人： Daniel G. Thompson , Steven James Vance , Jay A. Morrison
发明人： Daniel G. Thompson , Steven James Vance , Jay A. Morrison
IPC分类号： F01D9/00
CPC分类号： F04D29/388 , F01D5/147 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614 , Y10T428/249928 , Y10T428/249929
摘要： 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.
摘要翻译：本发明的实施例涉及一种由层叠翼型CMC层压板制成的坚固的涡轮叶片。每个层压板具有基本上垂直于面内方向的面内方向和贯穿厚度方向。层压板具有各向异性强度特性，其中面内拉伸强度基本上大于贯穿厚度拉伸强度。因此，层压板可以在高热梯度的方向上提供强度，并因此承受相关联的高热应力。层压板在贯穿厚度（层间）张力方面相对较弱，但是在操作中可以预期相对低的贯穿厚度的拉伸应力。层压板可以通过厚度压缩强; 因此，可以通过一个或多个紧固件将叠层叠层保持在通过厚度压缩中。 CMC材料可以允许包括额外的特征，例如冷却通道，肋，翼梁和热涂层，而不损害材料的强度特性。

6. 发明授权

US07247002B2 Lamellate CMC structure with interlock to metallic support structure 有权
标题翻译：层状CMC结构与金属支撑结构互锁
公开(公告)号：US07247002B2
公开(公告)日：2007-07-24
申请号：US11169477
申请日：2005-06-29
申请人： Harry A. Albrecht , Yevgeniy Shteyman , Jay A. Morrison , Daniel G. Thompson
发明人： Harry A. Albrecht , Yevgeniy Shteyman , Jay A. Morrison , Daniel G. Thompson
IPC分类号： F01D9/00
CPC分类号： F01D5/147 , F04D29/388 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614
摘要： A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperating interlock features (30, 32) formed on the lamella and on the support structure respectively. Mating load-transferring surfaces (34, 36) of the interlock features are disposed in a plane (44) oblique to local axes of thermal growth (38, 40) in order to accommodate differential thermal expansion there between with delta alpha zero expansion (DAZE). Reinforcing fibers (62) within the CMC material may be oriented in a direction optimized to resist forces being transferred through the interlock features. Individual lamellae may all have the same structure or different interlock feature shapes and/or locations may be used in different groups of the lamellae. Applications for this invention include an airfoil assembly (10) and a ring segment assembly (82).
摘要翻译：一种用于由由金属支撑结构（20）支撑的层叠多个陶瓷基体复合（CMC）薄片（12）形成的燃气涡轮发动机的部件（10）。单独的薄片通过分别形成在薄片上和支撑结构上的协同互锁特征（30,32）由支撑结构直接支撑。互锁特征的接合载荷传递表面（34,36）设置在与热生长（38,40）的局部轴线倾斜的平面（44）中，以便在其间容纳差分热膨胀，其中Δα零膨胀（DAZE ）。可以在CMC材料内的增强纤维（62）沿着优化的方向定向以抵抗通过互锁特征传递的力。单个薄片都可以具有相同的结构或不同的互锁特征形状，和/或位置可以用于不同的薄片组。本发明的应用包括翼型组件（10）和环形段组件（82）。

7. 发明授权

US4479735A Shrink fit sleeve for rotating machinery 失效
标题翻译：旋转机械的收缩套管
公开(公告)号：US4479735A
公开(公告)日：1984-10-30
申请号：US457787
申请日：1983-01-13
申请人： Daniel G. Thompson , Siu-Kee Chan
发明人： Daniel G. Thompson , Siu-Kee Chan
IPC分类号： F04D29/28 , F01D5/04 , F04D29/58 , F16D1/08 , F16C1/20
CPC分类号： F16D1/0835 , Y10T403/21 , Y10T403/217 , Y10T403/7047 , Y10T403/7061
摘要： Shrink fit sleeves 30 interposed between the hub 21 and the shaft 10 of a large rotating apparatus adapted for operation in an environment subject to severe cyclical loading as occasioned by large thermal transients, are provided with the property of having greater axial shear flexibility than radial flexibility and/or greater axial flexibility than that of the shrunk on component 21.
摘要翻译：插入在轮毂21和大型旋转装置的轴10之间的收缩套筒30适于在由于大的热瞬变引起的严重的循环负载的环境中操作，具有比径向柔性更大的轴向剪切挠度的性质和/或比组件21上收缩的更大的轴向挠性。

8. 发明授权

US4173429A Centrifugal fan, shaft, plate and hub assembly 失效
标题翻译：离心风机，轴，板和轮毂组件
公开(公告)号：US4173429A
公开(公告)日：1979-11-06
申请号：US857483
申请日：1977-12-05
申请人： Joseph H. Hoffman , Daniel G. Thompson
发明人： Joseph H. Hoffman , Daniel G. Thompson
IPC分类号： F01D5/02 , F04D29/28 , F04D29/58 , F16D1/076 , F04D17/08
CPC分类号： F01D5/025 , F04D29/281 , F16D1/076
摘要： A hub assembly for a centrifugal fan subjected to large transient thermal stresses is provided in which a pair of opposed hubs sandwich the inner peripheral margin of a disc-shaped fan plate, with the inner peripheral margin of the plate including a thickened ring portion to provide oppositely projecting annular shoulders at the outer periphery of the thickened ring portion, with the opposing hubs having annular recesses to receive the thickened ring portion and with the outer peripheries of the recesses in closely abutting relation with the shoulders to provide a shoulder-recess bearing area and with a plurality of fastener means extending through the hubs and through the thickened ring portion so that the shoulder-recess bearing area, which is located radially outwardly from the bearing stress areas at the bolt holes, largely receives the transient thermal stresses and therefore reduces the stress in the bolts and plate.
摘要翻译：提供一种用于经受大的瞬时热应力的离心式风扇的轮毂组件，其中一对相对的轮毂夹住盘形风扇板的内周边缘，板的内周边缘包括增厚的环部分，以提供相对的轮毂具有环形凹部以接纳增厚的环部分，并且凹部的外周与肩部紧密地邻接，以提供肩部凹陷承载区域并且具有多个紧固件装置，其延伸穿过轮毂并且穿过加厚的环部分，使得从螺栓孔处的轴承应力区域径向向外定位的肩部 - 凹槽支承区域很大程度上接收瞬态热应力，因此减小螺栓和板中的应力。

9. 发明授权

US07198458B2 Fail safe cooling system for turbine vanes 有权
标题翻译：涡轮叶片故障安全冷却系统
公开(公告)号：US07198458B2
公开(公告)日：2007-04-03
申请号：US11002029
申请日：2004-12-02
申请人： Daniel G. Thompson
发明人： Daniel G. Thompson
IPC分类号： F01D5/18
CPC分类号： F01D5/147
摘要： Embodiments of the invention relate to a turbine vane having a fail safe cooling system. According to embodiments of the invention, the vane can have multiple concentric layers of radial cooling holes extending about the vane; each layer being fluidly connected to the adjacent layer or layers. Such fluid communication can occur through one or more plenums in the vane or in the shrouds bounding the radial ends of the vane. Coolant can initially be supplied to the innermost layer of cooling holes. From there, the coolant can sequentially progress through successive outer layers. Between two adjacent layers, the coolant can flow in opposite directions. Not only does such a system provide needed cooling to the vane, but the multilayer redundant cooling system can avoid or delay catastrophic failures that can occur if the vane surface is damaged, such as by impact.
摘要翻译：本发明的实施例涉及具有故障安全冷却系统的涡轮叶片。根据本发明的实施例，叶片可以具有围绕叶片延伸的多个同心层的径向冷却孔; 每个层与相邻的层流体连接。这种流体连通可以通过叶片中的一个或多个增压室或限制在叶片的径向端部的护罩中发生。冷却液最初可以提供给最内层的冷却孔。从那里，冷却剂可以顺序地通过连续的外层进行。在两个相邻的层之间，冷却剂可以沿相反的方向流动。这样的系统不仅可以为叶片提供必要的冷却，而且多层冗余冷却系统可以避免或延迟如果叶片表面受到冲击而可能发生的灾难性故障。

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