涡轮式旋转爆震发动机有望为空天动力装置带来变革式性能提升，但其燃烧室内旋转爆震波所诱发的高频非定常环境，对燃烧室-涡轮的高效集成构成了严峻挑战。爆震波的状态参数对涡轮内部流动及叶片非定常气动激励具有关键影响，然而其频率变化的影响特征尚不明确。为此，本文基于运动激波模型构建了5kHz至20kHz范围内多种频率的入口爆震条件，系统研究了爆震波频率对涡轮流场时空演化与叶片气动激励特性的影响。结果显示，除典型的耙式激波包络外，导叶表面的后续反射波可形成更广义的上游反射波系；且激波扫掠频率越高，越难在上游激波的诱导下形成较强的下游波系。随着频率升高，流场的时域稳定性与空间均匀性均得到提升。在叶片气动激励方面，所有爆震频率下叶片表面局部压力的时均峰值与脉动幅值均显著高于均匀来流，但二者随频率升高呈下降趋势：相较于5kHz工况，20kHz工况的平均压力峰值和脉动幅值分别降低22.4%和46.1%。与此同时，叶栅时均载荷随频率增加而上升，而载荷的非定常脉动则随之降低，20kHz相对5kHz工况下降26.4%。研究表明，在本文涉及的频率范围内，提高爆震频率可促进燃烧室与涡轮的匹配并实现高气动负荷与低振动风险的设计平衡。

Turbine-based rotating detonation engines promise transformative performance enhancements for aerospace propulsion systems. However, the high-frequency unsteady environment induced by rotating detonation waves within the combustor poses a critical challenge for the efficient integration of the combustor and turbine. The characteristic parameters of detonation waves critically influence the internal turbine flow and unsteady blade aerodynamic excitation, yet the effects of frequency variation remain poorly understood. To address this issue, the present study establishes inlet detonation conditions with frequencies ranging from 5kHz to 20kHz based on a moving shock wave model, systematically investigating the influence of detonation wave frequency on the spatio-temporal evolution of the turbine flow field and blade aerodynamic excitation characteristics. The results demonstrate that, in addition to the typical rake-type shock envelope, subsequent reflected waves from the vane surfaces can form a more generalized upstream-propagating wave system. A higher shock sweeping frequency makes it more difficult for the upstream shock wave to induce a strong downstream wave system, but it enhances the temporal stability and spatial uniformity of the flow field. With regard to blade aerodynamic excitation, the time-averaged peak pressure and fluctuation amplitude on the blade surface far exceed those under uniform inflow at all detonation frequencies, but both decrease with increasing frequency: compared with the 5kHz case, the average pressure peak and fluctuation amplitude at 20kHz are reduced by 22.4% and 46.1%, respectively. Meanwhile, the time-averaged cascade load increases with frequency, whereas its unsteady fluctuation decreases, with a reduction of 26.4% at 20kHz relative to the 5kHz case. These findings indicate that, within the frequency range investigated, increasing the detonation frequency can facilitate combustor–turbine matching and achieve a design balance between high aerodynamic loading and low vibration risk.