FIELD: gas turbine engines.
SUBSTANCE: invention relates to a method for repairing a gas turbine engine blade, in particular a composite blade. A method for repairing a blade made of a composite material located in the axial direction, while said blade contains a root part and a feather, the axial end of which, opposite to the root part, contains a zone to be repaired, while said feather contains a trough surface and a back surface. The method comprises the steps of: a) placing a blade in the tool, b) positioning at least the first and second blades at the level of the repaired end zone, on the surface of the trough and on the surface of the back of the feather, each blade having an axial end opposite to the root part extending in the axial direction beyond the corresponding end of the pen and positioned relative to the control mark of the tool, while the specified end of each plate defines the axial end of the area to be repaired, while these plates limit the filling volume between themselves, c) the filling volume is filled with a pasty or fluid filling material d) the filling material is cured by heat treatment or polymerization of said material, e) the plates are removed.
EFFECT: fill volume plates determine the axial size of the area to be restored with the fill material, and there is no need for a machining operation after the fill material has solidified, thus avoiding the risk of damaging the restored area and also using a machining center.
9 cl, 7 dwg
