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19 条记录 (耗时 0.018 秒)

    Method for repairing turbine engine components
    1.
    发明授权
    Method for repairing turbine engine components 有权
    修理涡轮发动机部件的方法

    公开(公告)号：US06725540B2

    公开(公告)日：2004-04-27

    申请号：US10094702

    申请日：2002-03-09

    申请人： Sudhangshu Bose ,  Alan D. Cetel ,  Peter J. Draghi ,  Norman Pietruska

    发明人： Sudhangshu Bose ,  Alan D. Cetel ,  Peter J. Draghi ,  Norman Pietruska

    IPC分类号： B23P1500

    CPC分类号： C23G1/20 ,  B23P6/007 ,  C23C10/02 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49726 ,  Y10T29/49737 ,  Y10T29/49746

    摘要： The present invention relates to a method for repairing turbine engine components, such as vanes and blades, which have airfoils. The method broadly comprises removing oxidation debris from portions of the component by blending areas exhibiting thermal barrier coating spall and/or oxidation damage, removing a ceramic insulating layer from the component, and blending surfaces of the component where nicks, dents, and/or cracks are located. If the component has a depleted aluminum zone, the depleted zone is either removed or replenished. Further, a tip portion of the component, if damaged, is restored and tip abrasives are applied to restore the component's cutting ability. Thereafter, a ceramic coating is applied to the component.

    摘要翻译： 本发明涉及一种用于修理具有翼型的涡轮发动机部件（例如叶片和叶片）的方法。 该方法广泛地包括通过混合具有热障涂层剥落和/或氧化损伤的区域来除去部件的部分的氧化碎屑，从该组件中除去陶瓷绝缘层，以及混合表面，其中缺口，凹痕和/或裂纹 位于。 如果组件具有耗尽的铝区，则耗尽的区域被去除或补充。 此外，如果损坏的部件的尖端部分被恢复，并且施加尖端磨料以恢复部件的切割能力。 此后，将陶瓷涂层施加到部件上。

    High temperature composite material formed from nanostructured powders
    6.
    发明授权
    High temperature composite material formed from nanostructured powders 失效
    由纳米结构粉末形成的高温复合材料

    公开(公告)号：US06605556B1

    公开(公告)日：2003-08-12

    申请号：US08476497

    申请日：1995-06-07

    申请人： Sudhangshu Bose

    发明人： Sudhangshu Bose

    IPC分类号： C04B3580

    CPC分类号： C04B35/80

    摘要： The present invention relates to high temperature composite materials formed from nano-sized powders suitable for use in the manufacture of jet engine components. The composite materials consist essentially of a matrix formed from a powdered material having a particle size in the range of from about 1 to about 100 nanometers and a plurality of reinforcing fibers embedded within the matrix and comprising from about 20% to about 40% by volume of the composite material. The method of manufacturing the composite materials broadly comprises the steps of mixing the powdered material with the reinforcing fibers and consolidating the mixture to form the composite material.

    摘要翻译： 本发明涉及由适用于制造喷气发动机部件的纳米尺寸粉末形成的高温复合材料。 复合材料基本上由由粒度在约1至约100纳米范围内的粉末材料形成的基质和嵌入基质内的多个增强纤维组成，并且包含约20体积％至约40体积％ 的复合材料。 制造复合材料的方法广泛地包括将粉末材料与增强纤维混合并固结混合物以形成复合材料的步骤。

    Outer air seal for a gas turbine engine
    8.
    发明授权
    Outer air seal for a gas turbine engine 失效
    燃气轮机的外气密封

    公开(公告)号：US5304031A

    公开(公告)日：1994-04-19

    申请号：US28771

    申请日：1993-02-25

    申请人： Sudhangshu Bose

    发明人： Sudhangshu Bose

    IPC分类号： C23C16/04 ,  C23C16/32 ,  C23C16/44 ,  F01D11/12 ,  F01D11/08

    CPC分类号： C23C16/045 ,  C23C16/325 ,  C23C16/4418 ,  F01D11/122 ,  F05D2300/21 ,  F05D2300/603 ,  Y10S277/937 ,  Y10S277/943 ,  Y10T428/31678

    摘要： An uncooled turbine outer air is comprised of a combination of monolithic ceramics with high temperature capability and oxidation and creep resistance, and a fiber reinforced ceramic composite with high fracture toughness. In a preferred embodiment of the invention, a fiber reinforced ceramic composite of silicon carbide and aluminum borosilicate is infiltrated by chemically vapor deposited silicon carbide. The infiltration process is continued until the composite develops a monolithic layer of silicon carbide. An additional layer is deposited on the monolithic ceramic to provide additional thermal protection.

    摘要翻译： 未冷却的涡轮机外部空气由具有高温能力和抗氧化和抗蠕变性的整体式陶瓷的组合以及具有高断裂韧性的纤维增强陶瓷复合材料组成。 在本发明的优选实施方案中，碳化硅和硼硅酸铝的纤维增强陶瓷复合材料被化学气相沉积的碳化硅渗透。 渗透过程继续进行，直到复合材料开发出碳化硅的整体层。 另外的一层沉积在单片陶瓷上以提供额外的热保护。

    Corrosion resistant fuel cell substrates
    9.
    发明授权
    Corrosion resistant fuel cell substrates 失效
    耐腐蚀燃料电池基板

    公开(公告)号：US4985316A

    公开(公告)日：1991-01-15

    申请号：US432335

    申请日：1989-11-03

    申请人： Sudhangshu Bose ,  Michael E. Gorman

    发明人： Sudhangshu Bose ,  Michael E. Gorman

    IPC分类号： C04B35/524 ,  H01M4/96

    CPC分类号： H01M4/96 ,  C04B35/524 ,  Y10T428/30

    摘要： A porous substrate of a fuel cell electrode assembly is formed by producing a fibrous carbon precursor web by means of a conventional wet paper-making process. The precursor web is then dried and saturated with a wet resinous binder which will carbonize when heated. Substantially the entirety of all of the carbon fibers in the web are thus coated with the binder, and substantially all of the inter-fiber junctures in the web will also be coated with the binder. The saturated web is then dried, and heat treated to convert the binder to a glassy carbon which exhibits superior resistance to corrosion.

    摘要翻译： 燃料电池电极组件的多孔基底是通过常规的湿法造纸工艺生产纤维状碳前体纤维网而形成的。 然后将前体纤维网干燥并用湿树脂粘合剂饱和，该粘合剂将在加热时碳化。 因此，幅材中基本上全部的碳纤维都被粘合剂涂覆，并且幅材中基本上所有的纤维间接合面也将被粘合剂涂覆。 然后干燥饱和纤维网，并进行热处理以将粘合剂转化为显示出优异的耐腐蚀性的玻璃碳。