During the high temperature forging process, the thermal parameters such as the temperature field and strain field in the blank have an important influence on the crack damage and micro-structure in the forging. We use the rigid viscoelastic finite element method to carry out the forging process of a heavy aero-engine blade the finite element numerical simulation was carried out to obtain the temperature field, strain field and forging load change law in the forging process with time, and on this basis, combined with the crack damage and repair mechanism and the re­crystallization structure evolution law, an optimization was proposed. The forging process plan. That is, the pre-forging is performed on the basis of the tolerance of the final forging dimension under pressure of 4 mm, the pre-forging temperature is 1160°C, and the final forging temperature is 1120°C. The actual forging process test verifies the feasibility of the process plan, which is the engineering of this process the application lays the scientific foundation.