公开(公告)号：US20100151183A1

公开(公告)日：2010-06-17

申请号：US12316991

申请日：2008-12-17

申请人： Janet Davis ,  David Marshall ,  Olivier Sudre

发明人： Janet Davis ,  David Marshall ,  Olivier Sudre

IPC分类号： D03D27/00 ,  B32B7/02

CPC分类号： D03D25/005 ,  B32B3/30 ,  B32B5/024 ,  B32B5/26 ,  B32B9/005 ,  B32B2262/105 ,  B32B2262/106 ,  B32B2307/554 ,  B32B2581/00 ,  B32B2605/18 ,  Y10T428/23914 ,  Y10T428/23957 ,  Y10T428/23979 ,  Y10T428/23986 ,  Y10T428/24992 ,  Y10T428/24996 ,  Y10T428/249967

摘要： Devices, systems and methods for fabricating improved ceramic composite turbine shrouds with abradable seals are disclosed. A high temperature seal with an abradable coating is provided. The seal comprises a three-dimensional, high-density woven composite base structure recessed below the abradable coating, with loops incorporated in and protruding from the base structure. The abradable coating is integrally attached to the base structure via the loops. Additionally, a graded density seal is provided with a three-dimensional, low-density woven composite structure. The low-density structure is abradable. A three-dimensional, high-density woven composite base structure is recessed below the low-density structure, with the low-density structure integrally attached to the base structure via weaving.

摘要翻译： 公开了用于制造具有可磨损密封件的改进的陶瓷复合涡轮机护罩的装置，系统和方法。 提供了具有耐磨涂层的高温密封。 密封件包括在可磨损涂层下面凹陷的三维，高密度织造复合基底结构，其中结合到基部结构中并从基部结构突出。 可磨损涂层通过环一体地附接到基底结构。 此外，分级密度密封件设置有三维低密度编织复合结构。 低密度结构是可磨损的。 三维，高密度织造复合基底结构凹陷在低密度结构下方，低密度结构通过编织整体连接到基座结构。

公开(公告)号：US08309197B2

公开(公告)日：2012-11-13

申请号：US12316991

申请日：2008-12-17

申请人： Janet Davis ,  David Marshall ,  Olivier Sudre

发明人： Janet Davis ,  David Marshall ,  Olivier Sudre

IPC分类号： B32B7/02 ,  F01D11/08

CPC分类号： D03D25/005 ,  B32B3/30 ,  B32B5/024 ,  B32B5/26 ,  B32B9/005 ,  B32B2262/105 ,  B32B2262/106 ,  B32B2307/554 ,  B32B2581/00 ,  B32B2605/18 ,  Y10T428/23914 ,  Y10T428/23957 ,  Y10T428/23979 ,  Y10T428/23986 ,  Y10T428/24992 ,  Y10T428/24996 ,  Y10T428/249967

摘要： Devices, systems and methods for fabricating improved ceramic composite turbine shrouds with abradable seals are disclosed. A high temperature seal with an abradable coating is provided. The seal comprises a three-dimensional, high-density woven composite base structure recessed below the abradable coating, with loops incorporated in and protruding from the base structure. The abradable coating is integrally attached to the base structure via the loops. Additionally, a graded density seal is provided with a three-dimensional, low-density woven composite structure. The low-density structure is abradable. A three-dimensional, high-density woven composite base structure is recessed below the low-density structure, with the low-density structure integrally attached to the base structure via weaving.

摘要翻译： 公开了用于制造具有可磨损密封件的改进的陶瓷复合涡轮机护罩的装置，系统和方法。 提供了具有耐磨涂层的高温密封。 密封件包括在可磨损涂层下面凹陷的三维，高密度织造复合基底结构，其中结合到基部结构中并从基部结构突出。 可磨损涂层通过环一体地附接到基底结构。 此外，分级密度密封件设置有三维低密度编织复合结构。 低密度结构是可磨损的。 三维，高密度编织复合基底结构在低密度结构下面凹陷，低密度结构通过编织整体连接到基座结构。

公开(公告)号：US20070262201A1

公开(公告)日：2007-11-15

申请号：US11432865

申请日：2006-05-11

申请人： Brian Cox ,  Janet Davis ,  Sergio Lucato ,  David Marshall ,  Brock McCabe ,  Olivier Sudre

发明人： Brian Cox ,  Janet Davis ,  Sergio Lucato ,  David Marshall ,  Brock McCabe ,  Olivier Sudre

IPC分类号： B64B1/14

CPC分类号： B64C30/00 ,  B64D33/02 ,  B64D2033/026 ,  F02C7/042 ,  F05D2220/80 ,  F05D2300/2112 ,  F05D2300/224 ,  F05D2300/226 ,  F05D2300/2261 ,  F05D2300/228 ,  F05D2300/614 ,  Y02T50/672 ,  Y10T428/249928

摘要： An exemplary morphable ceramic composite structure includes a flexible ceramic composite skin and a truss structure attached to the skin. The truss structure can morph shape of the skin from a first shape to a second shape that is different than the first shape. The flexible ceramic composite skin may include a single-layer of three-dimensional woven fabric fibers and a ceramic matrix composite. The truss structure may include at least one actuatable element or an actuator may move a portion of the truss structure from a first position to a second position. A cooling component may be disposed in thermal communication with the skin. The cooling component may include thermal insulation or a cooling system that circulates cooling fluid in thermal communication with the skin. The morphable ceramic composite structure may be incorporated into any of an air inlet, combustor, exhaust nozzle, or control surfaces of a hypersonic aircraft.

摘要翻译： 示例性的变形陶瓷复合结构包括柔性陶瓷复合材料表皮和附着于皮肤的桁架结构。 桁架结构可以将皮肤的形状从第一形状变形为与第一形状不同的第二形状。 柔性陶瓷复合表皮可以包括单层三维织物纤维和陶瓷基复合材料。 桁架结构可以包括至少一个可启动元件，或者致动器可将桁架结构的一部分从第一位置移动到第二位置。 冷却部件可以设置成与皮肤热连通。 冷却部件可以包括热绝缘或冷却系统，其使冷却流体与皮肤热连通。 变形陶瓷复合结构可以结合到超音速飞机的空气入口，燃烧器，排气喷嘴或控制表面中的任何一个中。

公开(公告)号：US06251317B1

公开(公告)日：2001-06-26

申请号：US09284221

申请日：2000-01-13

申请人： Robert Lundberg ,  Magnus Holmquist ,  Anthony G. Razzell ,  Ludovic Molliex ,  Olivier Sudre ,  Michel Parlier ,  Fabrice Rossignol ,  Julien Parmentier

发明人： Robert Lundberg ,  Magnus Holmquist ,  Anthony G. Razzell ,  Ludovic Molliex ,  Olivier Sudre ,  Michel Parlier ,  Fabrice Rossignol ,  Julien Parmentier

IPC分类号： B29C6500

CPC分类号： C04B35/62873 ,  C04B35/117 ,  C04B35/62855 ,  C04B35/62892 ,  C04B35/62894 ,  C04B35/62897 ,  C04B35/645 ,  C04B35/803 ,  C04B2235/5224

摘要： The present method of manufacturing a ceramic composite material, composed of matrix and reinforcing materials and an intermediate weak interfice material, creates a composite material particuarly intended for use at temperatures above 1400° C. and in an oxidizing environment. The matrix and reinforcing materials consist of the same or different ceramic oxides having a melting point above 1600° C. The interface material provides in combination with the matrix and reinforcing materials a stress field liable to micro aciding. The reinforcing material is immersed into a powder slurry containing carbon (C) and ZrO2 so as to be coated thereby and then dried. After which, the thus created composite material is subjected to green forming and densifying steps. Finally, the composite material undergoes a heat-treatment in air leaving a porous structure of the interface material.

摘要翻译： 制造由基质和增强材料以及中间弱界面材料组成的陶瓷复合材料的现有方法产生特别地用于1400℃以上温度和在氧化环境中的复合材料。 基质和增强材料由熔点高于1600℃的相同或不同的陶瓷氧化物组成。界面材料与基体和增强材料组合提供易于微酸化的应力场。 将增强材料浸入含有碳（C）和ZrO 2的粉末浆料中，由此涂覆，然后干燥。 之后，将如此制得的复合材料进行绿色成型和致密化步骤。 最后，复合材料在空气中进行热处理，留下界面材料的多孔结构。

公开(公告)号：US20070252045A1

公开(公告)日：2007-11-01

申请号：US11380450

申请日：2006-04-27

申请人： Brian Cox ,  Janet Davis ,  Julia Mack ,  David Marshall ,  Peter Morgan ,  Olivier Sudre

发明人： Brian Cox ,  Janet Davis ,  Julia Mack ,  David Marshall ,  Peter Morgan ,  Olivier Sudre

IPC分类号： B64G1/52

CPC分类号： B64G1/58 ,  B64G1/14

摘要： A self-transpiring hot skin for a hypersonic or reusable space vehicle that can provide protection to the vehicle during short periods of abnormally high heat flux (either planned in the flight profile or an off-nominal event). The hot skin includes a ceramic composite structure having an internal cavity that is coupled either to the insulating layer or directly to the support structure of the hypersonic vehicle. The internal cavity includes a material system that vaporizes, sublimes or decomposes into a gas when the temperature exceeds the upper temperature capability of the composite material. The gas transpires through the outer layer of the composite material to provide cooling to the outer layer below the upper temperature capability. Cooling may occur both by conduction of heat from the composite material to the transpiring gas and by the interaction of the transpiring gas with the boundary layer of hypersonic flow over the outer surface, leading to a reduction of the heat flux entering the surface.

摘要翻译： 用于超音速或可重复使用的空中交通工具的自发热皮肤，可在短时间内异常高的热通量（在飞行情况下计划或非标称事件）中为车辆提供保护。 热皮肤包括具有内腔的陶瓷复合结构，其内部耦合到绝缘层或直接连接到超音速车辆的支撑结构。 内部空腔包括当温度超过复合材料的较高温度能力时气化，升华或分解成气体的材料体系。 气体通过复合材料的外层渗透，以便在较高温度能力以下向外层提供冷却。 冷却可以通过从复合材料传导到蒸发气体以及蒸发气体与外表面上的超音速流动边界层的相互作用而发生，导致进入表面的热通量减少。

公开(公告)号：US20070245534A1

公开(公告)日：2007-10-25

申请号：US11379677

申请日：2006-04-21

申请人： Olivier Sudre ,  Janet Davis ,  Stanley Lawton

发明人： Olivier Sudre ,  Janet Davis ,  Stanley Lawton

IPC分类号： B32B3/06 ,  B23P11/00

CPC分类号： A44B18/0038 ,  Y10T29/49826 ,  Y10T29/49948 ,  Y10T428/23993 ,  Y10T428/24017

摘要： A temperature tolerant hook and loop attachment, a method of forming a sheet of the hooks and, a method of insulating the skin of a flight vehicle. Temporary loops are formed in a fabric containing temperature tolerant fiber tows, e.g., the tows may be carbon, a metal, a carbide such as carbon silicide, a nitride, or an oxide. The temporary loops are stiffened (e.g., with resin, metal or ceramic), and severed to form temperature tolerant fiber composite hooks. The sheet may be cut and permanently applied, for example, to the skin of a spacecraft or aircraft. A fibrous material, e.g., fibrous insulation or batting, may be pressed in place or formed into the hooks, or the fibrous material may be attached to another structure and pressed in place for a temperature tolerant hook and loop attachment.

摘要翻译： 耐温钩钩环附件，形成钩片的方法，以及使飞行器的皮肤绝缘的方法。 在包含耐温纤维丝束的织物中形成临时环，例如，丝束可以是碳，金属，碳化硅如碳化硅，氮化物或氧化物。 临时环被加固（例如用树脂，金属或陶瓷），并且被切断以形成耐温纤维复合钩。 片可以被切割并永久地施加到例如航天器或飞行器的皮肤上。 纤维材料，例如纤维绝缘或棉絮，可以被压在适当位置或形成钩子，或者纤维材料可以附着到另一结构上，并被压在适当的位置，以实现耐温钩挂环。