| 发明名称 |
METHOD OF FABRICATING A COMPOSITE MATERIAL BLADE HAVING AN INTEGRATED METAL LEADING EDGE FOR A GAS TURBINE AEROENGINE |
| 摘要 |
A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method including in succession placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade, closing the injection mold, injecting a thermoplastic resin under pressure into the cavity of the mold so as to shape and overmold the metal strip, compacting the assembly, solidifying the resin by regulating the temperature of the injection mold, and unmolding the resulting blade. |
| 申请公布号 |
US2016167269(A1) |
申请公布日期 |
2016.06.16 |
| 申请号 |
US201414908321 |
申请日期 |
2014.07.22 |
| 申请人 |
SAFRAN |
发明人 |
PAUTARD Sebastien |
| 分类号 |
B29C45/14;F01D5/14;F01D5/28 |
主分类号 |
B29C45/14 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method comprising in succession:
placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade; closing the injection mold; injecting a filled thermoplastic resin under pressure into the cavity of the mold so as to shape and overmold the metal strip; compacting the assembly; solidifying the resin by regulating the temperature of the injection mold; and unmolding the resulting blade:, in which method the injection step is performed in a mold cavity having no fiber preform. |
| 地址 |
Paris FR |
