An iterative method was proposed for determining the cold blade profile from a hot blade profile based on the aerodynamic design. The method was applied to the design optimization of the gravity center tilting of a rotor blade. The optimization was based on the hot profile and the stress calculation on the cold profile. In that way

it could reduce the influence on the aerodynamic performance. A multi-objective optimization procedure of the gravity center tilting based on the commercial package iSIGHT was established by proposing a method of automatically updating the finite element mesh in the determination of cold blade profile. The effect of the disk on the optimization of gravity center tilting of a blade was investigated by referencing a swept fan blade with smaller hub-to-tip ratio. The results show that the maximum values of stress and deformation of a rotor blade are respectively decreased by 10.6% and 46% by the proposed method for a given hot profile from the aerodynamic design.