Abstract: THIS STUDY TAKES THE OUTER CASING COMPONENT OF A CERTAIN AIRCRAFT ENGINE GUIDE AS AN EXAMPLE, ANALYZING THE TEMPERATURE CHANGES, DEFORMATION, AND RESIDUAL STRESS OF PARTS AFTER WELDING THROUGH SIMULATION METHODS. THE FOCUS IS ON EXPLORING THE APPLICATION OF WELDING SIMULATION IN ACTUAL PRODUCTION PROCESSES. WHEN THE RESULTS OF WELDING SIMULATIONS CLOSELY RESEMBLE REAL-WORLD WELDING CONDITIONS, THEY PROVIDE VALUABLE GUIDANCE FOR PART PROCESSING.THE RESEARCH INDICATES THAT AFTER COMPLETING THE WELD SEAM 1, DUE TO THERMAL STRESS EFFECTS, THE DEFORMATION AT THE BOTTOM OF THE U-SHAPED RING IS APPROXIMATELY 0.23 MM, WHILE THE OVERALL DEFORMATION AT THE INSTALLATION EDGE IS ABOUT 0.18 MM. THE AREAS WELDED FIRST ARE SUBJECT TO MORE COMPLEX DEFORMATIONS INFLUENCED BY HEAT ACCUMULATION FROM SUBSEQUENT WELDS. THE ABILITY OF PARTS TO RESIST DEFORMATION IS AFFECTED BY SEVERAL FACTORS INCLUDING WELDING TEMPERATURE, PART STRUCTURE, MATERIAL THICKNESS, AND LOAD APPLICATION TIME.UNDER CONSISTENT CONDITIONS, HIGHER WELDING TEMPERATURES RESULT IN REDUCED RESISTANCE TO DEFORMATION; POST-WELD COMPONENTS ARE MORE PRONE TO SIGNIFICANT CHANGES IN STRUCTURALLY COMPLEX REGIONS; GREATER MATERIAL THICKNESS ENHANCES RESISTANCE AGAINST DEFORMATION; AND LONGER DURATIONS FOR APPLYING LOADS AFTER WELDING MAKE IT LESS LIKELY FOR PARTS TO DEFORM.