The invention relates to the technical field of
alloy dissimilar materials, in particular to a high-temperature
alloy dissimilar material
welding method for a gas
turbine, which comprises the following steps: S1, mechanically
grinding and
polishing the to-be-welded surfaces of an
alloy dissimilar material A and an alloy dissimilar material B, and then ultrasonically cleaning and
drying for later use; s2, preparing a modified
molybdenum-based composite layer; s3, a sample is cooled in vacuum, then high-purity
argon is introduced, the sample is taken out and assembled with the alloy dissimilar material B obtained in the step S1 in a
butt joint mode, and modified
brazing filler metal powder is placed; and S4, the sample in the step S2 is placed in a vacuum
brazing furnace, vacuumizing is conducted, the temperature is slowly increased to 1300 DEG C, heat preservation is conducted, the temperature is slowly decreased to the
room temperature in a furnace cooling mode, and then
welding is completed. The wettability of the
brazing filler metal to
base metal is remarkably improved,
diffusion and
solid solution among elements are promoted, and the tensile strength of a joint is remarkably improved. And meanwhile, a vacuum brazing process is adopted, and precise temperature and
time control is matched, so that oxidation and
pollution are avoided, and the stability and
repeatability of
welding quality are ensured.