发明名称 |
Method for repairing gas turbine rotor blades |
摘要 |
A method for replacing a portion of a gas turbine engine rotor blade, the rotor blade having a contour defined by a blade first sidewall (70) and a blade second sidewall (70) includes cutting through the rotor blade such that a cut line (110) extends from a leading edge (74) of the blade to a trailing edge (76) of the blade, and between the first sidewall and the second sidewall, removing the portion of the rotor blade that is radially outward of the cut line, and coupling a replacement blade portion (120) to remaining blade portion (98) such that the newly formed rotor blade (150) is formed with a predetermined aerodynamic contour. <IMAGE> |
申请公布号 |
EP1533071(A2) |
申请公布日期 |
2005.05.25 |
申请号 |
EP20040256954 |
申请日期 |
2004.11.10 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
TREWILER, GARY EDWARD;FERRIGNO, STEPHEN JOSEPH;WILKINS, MELVIN HOWARD;STEWART, MATTHEW |
分类号 |
F01D5/12;B23K9/00;B23P6/00;F01D5/00;F01D25/00;F02C7/00;F04D29/38;(IPC1-7):B23P6/00 |
主分类号 |
F01D5/12 |
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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