| Citation: | DU Jiatong, WANG Yong, PENG Yerong, et al. Research on the overall parameter optimization design method of turboshaft engine based on helicopter mission requirements[J]. Journal of Aerospace Power, 2025, 40（10）：20230417 doi: 10.13224/j.cnki.jasp.20230417
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In view of the problem of insufficient consideration of helicopter/engine coupling relationship in the traditional overall parameter design process of turboshaft engines and the lack of boundary restrictions on the feasible region of alternative design parameters, a method for optimizing the overall parameters of turboshaft engines was proposed based on the requirements of helicopter flight missions, and the feasible region of design parameter optimization was reasonably limited according to the development of turboshaft engines. The method consisted of four modules: constraint analysis, task analysis, parameter cycle calculation and optimization iteration. The optimization iteration module involved dynamic adjustment of design parameters, which made the designed engine more matched with the task requirements. Firstly, the basic principles of the above four modules were derived. Then, based on the given helicopter flight mission profile, the proposed design method was verified by an example. Finally, the results were compared with other design methods for the same flight mission. The research showed that the proposed feasible region boundary of design parameters can reasonably limit the selection range of design parameters and can be used as a basis for the selection of design parameters. The proposed optimization design method of the overall parameters of the turboshaft engine made up for the shortcomings of other overall design methods of the turboshaft engine, for example, the design parameters were not involved in the iterative update and the lack of consideration of the coupling relationship between the helicopter / turboshaft engine performance.
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