Abstract: 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.

Key words: Gas turbine engine；Compressor disk；Structure design；Evolutionary structural method；Topology optimization

摘要： 为填补国内发动机设计体系初始阶段的不足，基于渐进结构法建立了一套适用于燃气发动机压气机转子轮盘的拓扑优化设计方法，充分考虑工程需求，对优化过程中可能出现的主结构断裂、封闭环腔结构问题，以及优化过程不可逆的缺陷，分别提出了限定全局与优化子步中可优化域、人为控制优化进程等应对措施。以轮缘径向位移协调为目标的算例表明，该方法有效提高了轮盘处内流道的保形效果，具有流程可行性与结果有效性，从而具备良好的工程实用性。

关键词: 燃气涡轮发动机；压气机轮盘；结构设计；渐进结构法；拓扑优化