Topology optimization design method on compressor disks in gas turbine engines

To fill up the deficiency in the initial phase of the domestic gas turbine engine design system, based on evolutionary structural method, a topology optimization method suitable for compressor disks of gas turbine engines was developed. With full consideration on engineering demand, to solve the problem such as breakage of main structure, closed looping cavity structure, and the imperfection of irreversibility of optimization algorithm that may be encountered during optimization progress, a series of solutions, including limiting both overall and per-step optimization fields, artificially controlling the progress of optimization, were put forward. The numerical example treating coordinating radial displacement on flange as the objective proves that the optimization method improves the shape-preserving effect of inner-side flow passage composed by the flange of disk. Therefore, it demonstrates that the optimization method possesses satisfactory engineering practicability with feasibility on its process and effectiveness on its result.