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    • 6. 发明授权
    • Turbine blade tip shroud enclosed friction damper
    • 涡轮叶片顶盖封闭式摩擦阻尼器
    • US06371727B1
    • 2002-04-16
    • US09587553
    • 2000-06-05
    • Maynard L. StangelandClifford C. Bampton
    • Maynard L. StangelandClifford C. Bampton
    • F01D510
    • F01D5/225F01D5/22Y02T50/673Y10S416/50
    • A turbine disk assembly having an integrally bladed turbine disk and a plurality of captured damper members. The integrally bladed turbine disk includes a plurality of turbine blades that terminate at an integral tip shroud. A damper aperture is formed between each pair of adjacent integral tip shrouds and includes a first slotted portion and a second slotted portion. The first slotted portion is formed concentric to the two adjacent integral tip shrouds, extending circumferentially and axially through the two adjacent integral tip shrouds. The second slotted portion extends radially outwardly between the two adjacent integral tip shrouds. One of the damper members is disposed in the first slotted portion of the an associated damper aperture and frictionally engages at least one surface of each of the two adjacent tip shrouds to dissipate energy when relative motion occurs between the two adjacent integral tip shrouds to dampen vibration.
    • 一种涡轮盘组件,其具有整体叶片涡轮盘和多个捕获的阻尼器构件。 一体式叶片式涡轮盘包括终止于整体顶端罩的多个涡轮机叶片。 在每对相邻的整体尖端护罩之间形成阻尼器孔,并包括第一开槽部分和第二开槽部分。 第一开槽部分与两个相邻的整体尖端护罩同心地形成,沿周向和轴向延伸穿过两个相邻的整体尖端护罩。 第二开槽部分在两个相邻的整体尖端护罩之间径向向外延伸。 阻尼器构件中的一个设置在相关联的阻尼器孔的第一开槽部分中并且摩擦地接合两个相邻尖端护罩中的每一个的至少一个表面,以在两个相邻的整体尖端护罩之间发生相对运动以消除振动时消散能量 。
    • 7. 发明授权
    • Free form fabrication of metallic components
    • 自由形成金属部件
    • US5745834A
    • 1998-04-28
    • US530770
    • 1995-09-19
    • Clifford C. BamptonRobert BurkettHong-Son Ryang
    • Clifford C. BamptonRobert BurkettHong-Son Ryang
    • B22F3/02B22F3/10B22F3/105B29C67/00B22F1/00
    • B22F3/1055B22F3/10B22F2003/1042B22F2998/00B22F2998/10B29K2503/06Y02P10/295
    • A method of free form fabrication of metallic components, typically using computer aided design data, comprises selective laser binding and transient liquid sintering of blended powders. The powder blend includes a base metal alloy, a lower melting temperature alloy, and a polymer binder that constitutes approximately 5-15% of the total blend. A preform part is built up, layer-by-layer, by localized laser melting of the polymer constituent, which rapidly resolidifies to bind the metal particles. The binder is eliminated from the preform part by heating in a vacuum furnace at low atmospheric pressure. The preform part may require support during elimination of the polymer binder and subsequent densification by controlled heat treatment. Densification is performed at a temperature above the melting point of the lower temperature alloy but below the melting point of the base metal alloy to produce transient liquid sintering of the part to near full density with desired shape and dimensional tolerances. The densified part may be subjected to a final hot isostatic pressing (HIP) treatment to close residual porosity and complete the chemical homogenization of the part. Elimination of residual porosity improves fatigue properties of part, and homogenization improves ambient temperature ductility, toughness, and high temperature strength. An advantage of the process is rapid production of complex shaped metal prototypes and complete small batch production runs of high cost metal components without special tooling or machining operations.
    • 通常使用计算机辅助设计数据的金属部件的自由形状制造方法包括选择性激光结合和混合粉末的瞬态液体烧结。 粉末混合物包括贱金属合金,较低熔点的合金和构成总混合物的约5-15%的聚合物粘合剂。 通过聚合物成分的局部激光熔化,逐层地形成预制件部分,其快速重新固化以结合金属颗粒。 通过在低压大气压下在真空炉中加热,从预制件部件中除去粘合剂。 预制件部件在消除聚合物粘合剂期间可能需要支撑,并且随后通过受控热处理致密化。 在低于合金的熔点但低于母材金属合金的熔点的温度下进行致密化,以产生具有所需形状和尺寸公差的部分到接近全密度的瞬态液体烧结。 致密部分可以进行最终的热等静压(HIP)处理,以闭合残余孔隙率并完成部件的化学均质化。 消除残留孔隙度可以改善零件的疲劳性能,均质化可提高环境温度的延展性,韧性和高温强度。 该工艺的优点是快速生产复杂形状的金属原型,并在没有特殊的加工或加工操作的情况下完成小批量生产的高成本金属零件。