| 发明名称 |
METHOD FOR PRODUCING A METAL PART FOR AN AIRCRAFT TURBO-ENGINE |
| 摘要 |
A method for producing a metal part, the part including, in particular, a first set of elements having a small thickness, and a second set of elements having a large thickness, the method including: forming a peripheral portion of the elements of the second set of elements by selectively melting a powder by scanning the surface of the powder layer with a laser beam or with an electron beam; using the peripheral portion of the elements of the second set of elements as a mould by carrying out an operation of filling an inner area defined by the peripheral portion with liquid metal; cooling the metal part to solidify the inner area defined by the peripheral portion and filled with metal. |
| 申请公布号 |
US2014262124(A1) |
申请公布日期 |
2014.09.18 |
| 申请号 |
US201214354182 |
申请日期 |
2012.10.24 |
| 申请人 |
SNECMA |
发明人 |
Vilaro Thomas;Rix Sebastien;Baudimont Cyrille |
| 分类号 |
B22D23/06;B22D25/02;B23P15/02 |
主分类号 |
B22D23/06 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. Method for producing a metal part, said part comprising a first set of elements having a small thickness comprised between 0.3 millimetres and 4 millimetres, and a second set of elements having a large thickness greater than four millimetres, the metal part being a part of an aircraft turbo-engine, said method comprising:
forming a peripheral portion of the elements of the second set of elements by selectively melting a metal powder by scanning a surface of a powder layer with a laser beam or with an electron beam; using the peripheral portion of the elements of the second set of elements as a mould by carrying out an operation of filling an inner area defined by said peripheral portion with liquid metal; cooling the metal part to solidify the inner area, defined by the peripheral portion and filled with metal. |
| 地址 |
Paris FR |
