Patent ID: 7293964

Claim:
A repair method for a blade of a turbomachine, in which at least a partial area of a leading edge of the blade is removed, comprising: making a cutback on the blade between two points (A) and (E) whose positions on an original profile of a leading edge of the blade follow the following relationship: point (A) is a starting point and lies within a range of a relative blade height (h/H) of 0≦(h/H) point A <0.85, and point (E) is an end point and lies within a range of the relative blade height (h/H) of 0.95<(h/H) point E ≦1.0, wherein, (h) is a blade height coordinate which originates at an end of the blade which is closer to the starting point (A), and in which (H) is the blade height, a trace of the cutback is defined by a relationship of relative cutback position (s/S AE ) and relative cutback length (c/C m ), with (c) being a local cutback length in meridional flow direction, (C m ) being a meridional chord length, (s) being a local cutback length in radial direction, and (S AE ) being a radial cutback length, and, the local cutback length (c) gradually increases from point (A) to its maximum within the range of 0.60<(s/S AE )<0.95, with the relative cutback length (c/C m ) there amounting to (c/C m )≦0.25, and with the relative cutback length (c/C m ) then decreasing to (c/C m )≦0.05.