发明名称 Method of manufacturing a hollow blade for a turbomachine
摘要 The procedure consists of assembling the primary components (11) and placing them in a furnace, subjecting to pre-baking and eliminating the binding agent of the anti-diffusion product. Then, without moving the components, the interior of the blade assembly (14) is subjected to a vacuum and a simultaneous increase in temperature to produce a permanent plastic deformation of the components. The interior of the blade assembly, made from a titanium alloy, is kept under the vacuum while an isostatic pressure is applied to the exterior, with the pressure and temperature conditions maintained to ensure a compaction of the anti-diffusion product and a pre-welding of the non-coated zones of the diffusion barrier. The assembly is subsequently inflated by gas pressure and superplastically moulded before subjecting to final machining.
申请公布号 IL121982(A) 申请公布日期 2000.12.06
申请号 IL19970121982 申请日期 1997.10.15
申请人 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION "SNECMA" 发明人
分类号 B21D26/02;B21D26/021;B21D26/055;B21D53/78;B23K20/00;B23K20/18;B23P15/04;F01D5/18;F01D25/00;F04D29/38;(IPC1-7):B23P15/00 主分类号 B21D26/02
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