Turbine and compressor disks producing method for aircraft gas turbine, involves adjusting surface property for obtaining high or low amount heat transmission and residual stresses in specific surface regions of forging contour

摘要

The method involves subjecting a forging blank including a specific forging contour to heating and cooling processes. The forging blank is formed for attaining specific temperature gradient during cooling process and for selectively influencing rate and distribution of pressure and internal tensile stress in a surface property. Rate and distribution of residual stresses existing in a structural contour are detected and evaluated. The surface property is adjusted for obtaining high or low amount heat transmission and residual stresses in specific surface regions of the forging contour.