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    • 9. 发明授权
    • Method of manufacturing a blade
    • 制造刀片的方法
    • US5711068A
    • 1998-01-27
    • US735106
    • 1996-10-22
    • Frank Trevor Salt
    • Frank Trevor Salt
    • B23P15/04B23P15/00
    • B23P15/04Y10T29/49318Y10T29/49339
    • A preform of a superplastically formed fan blade for a turbofan aeroengine, includes two blade flank components and a core sheet sandwiched between them. A manufacturing process for producing the blade preforms comprises cutting titanium plate material into rectangular prism shaped pieces of suitable length and thickness. Each piece is cut lengthwise along an inclined plane to form two separate tapered panels which become the blade flank components. After machining to a three dimensional profile on the cut faces, pairs of the blade flank components are stacked together with their uncut surfaces confronting each other, the core sheet being placed between them. The blade flank components are then diffusion bonded to the core sheet in a predefined pattern so as to create the blade preform with an internal structure defined by the bonding pattern. The blade preform can then be superplastically formed and finish machined to produce the fan blade.
    • 用于涡轮风扇航空发动机的超塑性风扇叶片的预制件包括两个叶片侧面部件和夹在它们之间的芯板。 用于制造刀片预制件的制造方法包括将钛板材切割成具有合适长度和厚度的矩形棱柱形件。 每个片段沿着倾斜平面被纵向切割以形成两个单独的锥形面板,其成为刀片侧面部件。 在切割面上加工成三维轮廓之后,将成对的刀片侧面部件与彼此面对的未切割表面堆叠在一起,将芯片放置在它们之间。 然后叶片侧面部件以预定图案扩散粘结到芯片上,以便产生具有由结合图案限定的内部结构的刀片预制件。 然后可以将叶片预制件超塑性地形成并精加工以产生风扇叶片。