FIELD: metallurgy.
SUBSTANCE: invention relates to metal parts (301) surfacing method for aircraft turbojet engine and tooling for its implementation. Metal part is set into surfacing (301) position in chamber (201), having upper part (202) with hole (208). Movable cover (221) with hole (222) is installed on hole (208) in chamber upper part (202). Performing nozzle (103) positioning on movable cover (221) hole (222) level. Introducing inert gas into chamber (201). Performing metal powder application on metal part (301), laser beam or electrons beam emission for metal part (301) surfacing, applied powder warming up by said beam with provision of metal part (301) surfacing. During surfacing process performing nozzle (103) movement relative to chamber (201) in accordance with metal part (301) surfacing path, wherein by nozzle (103) displacement performing movable cover (201) movement on chamber (201) upper part (202).
EFFECT: result is provision of considerable rectilinear nozzle movement, which enables to cover entire surfacing area, as well as insulation, which prevents fast gas flow from chamber, accordingly preventing part oxidation during surfacing.
14 cl, 5 dwg
