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1. 发明申请

US20070128043A1 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：US20070128043A1
公开(公告)日：2007-06-07
申请号：US11040464
申请日：2005-01-21
申请人： Jay Morrison , Gary Merrill , Steven Vance , Harry Albrecht , Yevgeniy Shteyman
发明人： Jay Morrison , Gary Merrill , Steven Vance , Harry Albrecht , Yevgeniy Shteyman
IPC分类号： F03B3/12
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。

2. 发明申请

US20070140835A1 COOLING SYSTEMS FOR STACKED LAMINATE CMC VANE 有权
标题翻译：堆叠层压CMC VANE冷却系统
公开(公告)号：US20070140835A1
公开(公告)日：2007-06-21
申请号：US11002030
申请日：2004-12-02
申请人： Harry Albrecht , Yevgeniy Shteyman , Steven Vance , Jay Morrison
发明人： Harry Albrecht , Yevgeniy Shteyman , Steven Vance , Jay Morrison
IPC分类号： F03B11/00
CPC分类号： F01D5/147 , F01D5/187 , F01D5/284 , F05D2260/201 , F05D2300/501 , F05D2300/603 , F05D2300/702
摘要： Embodiments of the invention relate to various cooling systems for a turbine vane made of stacked ceramic matrix composite (CMC) laminates. Each airfoil-shaped 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. Such a vane construction lends itself to the inclusion of various cooling features in individual laminates using conventional manufacturing and forming techniques. When assembled in a radial stack, the cooling features in the individual laminates can cooperate to form intricate three dimensional cooling systems in the vane.
摘要翻译：本发明的实施例涉及由堆叠的陶瓷基质复合（CMC）层压体制成的涡轮叶片的各种冷却系统。每个翼型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。这种叶片结构使得能够使用常规的制造和成形技术将各种冷却特征包含在单独的层压板中。当组装成径向堆叠时，单个层压板中的冷却特征可以协作以在叶片中形成复杂的三维冷却系统。

3. 发明申请

US20070020105A1 Lamellate CMC structure with interlock to metallic support structure 有权
公开(公告)号：US20070020105A1
公开(公告)日：2007-01-25
申请号：US11169477
申请日：2005-06-29
申请人： Harry Albrecht , Yevgeniy Shteyman , Jay Morrison , Daniel Thompson
发明人： Harry Albrecht , Yevgeniy Shteyman , Jay Morrison , Daniel Thompson
IPC分类号： B64C27/46
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).

4. 发明申请

US20050238491A1 Ceramic matrix composite airfoil trailing edge arrangement 有权
标题翻译：陶瓷基复合翼面后缘布置
公开(公告)号：US20050238491A1
公开(公告)日：2005-10-27
申请号：US10830384
申请日：2004-04-22
申请人： Jay Morrison , Harry Albrecht , Yevgeniy Shteyman , Thomas Jackson
发明人： Jay Morrison , Harry Albrecht , Yevgeniy Shteyman , Thomas Jackson
IPC分类号： B63H1/26 , F01D5/18 , F01D5/28
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。

5. 发明申请

US20060171812A1 Support system for a composite airfoil in a turbine engine 有权
标题翻译：涡轮发动机复合翼型支撑系统
公开(公告)号：US20060171812A1
公开(公告)日：2006-08-03
申请号：US11049241
申请日：2005-02-02
申请人： Harry Albrecht , Yevgeniy Shteyman
发明人： Harry Albrecht , Yevgeniy Shteyman
IPC分类号： F01D5/26
CPC分类号： F01D5/147 , F05D2230/64
摘要： A turbine airfoil support system for coupling together a turbine airfoil formed from two or more components, wherein the support system is particularly suited for use with a composite airfoil. In at least one embodiment, the turbine airfoil support system may be configured to attach shrouds to both ends of an airfoil and to maintain a compressive load on those shrouds while the airfoil is positioned in a turbine engine. Application of the compressive load to the airfoil increases the airfoil's ability to withstand tensile forces encountered during turbine engine operation.
摘要翻译：一种用于将由两个或更多个部件形成的涡轮机翼型件联接在一起的涡轮机翼型支撑系统，其中所述支撑系统特别适用于复合翼型件。在至少一个实施例中，涡轮机翼型支撑系统可以被配置成将翼片附接到翼型件的两端并且在翼型件定位在涡轮发动机中时保持在这些护罩上的压缩载荷。压缩载荷对翼型的应用增加了翼型在承受涡轮发动机运行过程中遇到的张力的能力。

6. 发明申请

US20060171809A1 Cooling fluid preheating system for an airfoil in a turbine engine 有权
标题翻译：涡轮发动机翼型的冷却液预热系统
公开(公告)号：US20060171809A1
公开(公告)日：2006-08-03
申请号：US11049239
申请日：2005-02-02
申请人： Harry Albrecht , Yevgeniy Shteyman
发明人： Harry Albrecht , Yevgeniy Shteyman
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F05D2240/81 , F05D2260/205 , F05D2300/603
摘要： A platform cooling system usable in a turbine engine together with an airfoil for preheating cooling fluids before the cooling fluids enter a cooling system in the airfoil in a turbine engine. The platform cooling system includes cooling channels in either the ID or OD platforms, or both, of the airfoil. The channels transfer heat to the cooling fluids flowing through the platform cooling system and thereby heat the cooling fluids. The preheated cooling fluids are particularly useful with cooling composite ceramic airfoils, which are susceptible to damage from large temperature gradients developed between combustion gases outside the airfoil and cooling fluids inside the airfoil. The platform cooling system may be combined with an airfoil cooling system to create a serial cooling system in which cooling fluids may enter the platform and flow through the platform and airfoil without being supplemented with additional cooling fluids along the flow path.
摘要翻译：一种平台冷却系统，其可用于涡轮发动机和翼型件，用于在冷却流体进入涡轮发动机的翼型中的冷却系统之前预热冷却流体。平台冷却系统包括翼型的ID或OD平台或两者的冷却通道。通道将热量传递到流过平台冷却系统的冷却流体，从而加热冷却流体。预热的冷却流体特别适用于冷却复合陶瓷翼型件，这些翼型件易受到在翼型外部的燃烧气体和翼型内的冷却流体之间产生的大的温度梯度的损害。平台冷却系统可以与翼型冷却系统组合以产生串联冷却系统，其中冷却流体可以进入平台并流过平台和翼型件，而不沿着流动路径补充另外的冷却流体。

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