Abstract: The crack in the turbine vanes of the aircraft engine generated during service can be repaired by powder metallurgy repair technology. The filler powders with different compositions and sizes were designed aiming at the material and structure of the low press turbine vanes of K417G alloy to be repaired. Tap density of powders with different mesh sizes and mixture ratios were tested. The performance values of sintered samples, such as porosity, mean pore diameter, median pore diameter, mode pore diameter were obtained by metallographic examination and mercury porosimetry. The optimal filler powders were determined by using the above investigations. The microstructure and performance of powder metallurgy repair joints were analyzed. The results showed that the specimen were repaired well and there was no defect in the joint.