| Citation: | ZHENG Longxi, LIU Kexin, LU Jie, et al. Research progress on turbine performance and optimization strategy under pulse detonation gas impact[J]. Journal of Aerospace Power, 2025, 40（10）：20240471 doi: 10.13224/j.cnki.jasp.20240471
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The intensely unsteady exhaust flow from pulse detonation combustor has a significant impact on turbine performance. The matching problem between pulse detonation combustor and turbine components is one of the difficulties restricting the development of pulse detonation turbine engine. In order to clarify the research progress on turbine performance and optimization strategies under pulse detonation gas impact, the flow characteristics and evolution process of exhaust flow field were briefly introduced with the pulse detonation combustor exhaust characteristics as the starting point. From the aspects of theoretical analysis, experimental testing and numerical simulation, the research status of key issues such as turbine performance evaluation methods, turbine operating characteristics, turbine internal flow characteristics and loss mechanism under pulse detonation gas impact was summarized. The research achievements of Northwestern Polytechnical University in the field of pulse detonation combustor and turbine component matching were reviewed, and the key problems to be solved in this field were prospected. Optimization strategies for turbine performance under pulse detonation gas impact were proposed, including stabilized pressure device, shock attenuation device, and turbine blade optimization design, etc. This indicates that the organic integration of various optimization strategies is one of the future research directions.
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