发明名称 |
Method of making a hollow blade for a turbomachine having a release material after welding |
摘要 |
The procedure for fabricating a blade for a turbine engine involves using computer assistance, for providing a digital simulation to construct the flat components of the blade. The elementary pieces of the blade are forged and machined. A diffusion barrier layer is then applied to the blade, in order to determine the final internal geometry of the blade, and the components are assembled using a diffusion welding process under iso-static pressure. The components are then inflated under gas pressure in order to form the blade shape, in a super-plastic mode, prior to final machining. The process also includes an additional complementary stage of un-gluing parts of the blade structure internally, with this region being defined by the diffusion barrier layer applied previously. The un-gluing process enables the formation of internal cavities in the blade structure. |
申请公布号 |
EP0824048(A1) |
申请公布日期 |
1998.02.18 |
申请号 |
EP19970401926 |
申请日期 |
1997.08.13 |
申请人 |
SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION, "S.N.E.C.M.A." |
发明人 |
CALLE, GILLES MICHEL GEORGES LOUIS;KLEIN, GILLES CHARLES |
分类号 |
B23P15/02;B21D26/02;B21D26/027;B21D26/055;B21D53/78;C22F1/00;C22F1/18;F01D5/18;F02C7/00;(IPC1-7):B21D26/02 |
主分类号 |
B23P15/02 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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