| Citation: | NIE Jiayi, WU Yuwen, WENG Chunsheng, et al. Numerical study on interaction between rotating detonation backpressure and axial compressor[J]. Journal of Aerospace Power, 2025, 40（6）：20230620 doi: 10.13224/j.cnki.jasp.20230620
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A coupled computational model of a transonic axial compressor and a rotating detonation combustor Stage 37 was constructed to investigate the impact of forward-propagating pressure waves generated by rotating backpressure on the internal flow field of the compressor. Furthermore, the effect of backpressure velocity on the compressor's performance was analyzed. It was observed that the forward-propagating wave interacted with both the stator and rotor blades, resulting in a slight upstream shift in the attached shockwave at the leading edge of the rotor blades due to the influence of the rotating backpressure. Moreover, the flow field structure of the stator was more significantly affected by rotational backpressure, and correspondingly, the forward pressure wave was relatively more strongly suppressed by the stator. In comparison with the peak efficiency point, the compressor’s performance was found that CJ velocity backpressure (CJ was the detonation propagation velocity in the Chapman-Jouguet theory) had a positive effect on the compressor’s efficiency, with an increase of 1% and wider operating range.
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