This article, in order to improve the deformation homogeneity in aerospace forgings, proposes an approach that combines the fnite element method （FEM） and the response surface method （RSM） to optimize the preform ...This article, in order to improve the deformation homogeneity in aerospace forgings, proposes an approach that combines the fnite element method （FEM） and the response surface method （RSM） to optimize the preform shapes. New expressions that take into account the influences of equivalent effective strain distribution are developed to evaluate the homogeneity of deformation distribution in aerospace forgings. In order to reduce the number of design variables, the domain-division method is put forward to determine the optimal design variables. On the basis of FEM results, the RSM is used to establish an approximate model to depict the relationship between the responses （deformation homogeneity and die underfilling） and the design variables repre- sented by geometric parameters of the preform shape. With a typical aeroengine disk as an example, the proposed method is verified by achieving an optimal combination of design variables. By comparing the preform shape obtained with the proposed method to that with the existing one, it is evidenced that the former could achieve more homogeneous deformation in forging.展开更多
文摘This article, in order to improve the deformation homogeneity in aerospace forgings, proposes an approach that combines the fnite element method （FEM） and the response surface method （RSM） to optimize the preform shapes. New expressions that take into account the influences of equivalent effective strain distribution are developed to evaluate the homogeneity of deformation distribution in aerospace forgings. In order to reduce the number of design variables, the domain-division method is put forward to determine the optimal design variables. On the basis of FEM results, the RSM is used to establish an approximate model to depict the relationship between the responses （deformation homogeneity and die underfilling） and the design variables repre- sented by geometric parameters of the preform shape. With a typical aeroengine disk as an example, the proposed method is verified by achieving an optimal combination of design variables. By comparing the preform shape obtained with the proposed method to that with the existing one, it is evidenced that the former could achieve more homogeneous deformation in forging.
