| Citation: | DUAN Wenhua, CHEN Weijie, ZHAO Xinyu, et al. Experiment of turbine cascade under high Mach number and low Reynolds number conditions[J]. Journal of Aerospace Power, 2024, 39（10）：20220827 doi: 10.13224/j.cnki.jasp.20220827
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A high speed low pressure turbine cascade was experimentally and numerically studied under high Mach number and low Reynolds number conditions. The loss characteristics of cascade under isentropic outlet Mach number range of 0.66—1.23 and Reynolds number range of 1.1×105—9.0×105 were studied experimentally, and the flow field under typical conditions was simulated. The influence of Reynolds number on cascade performance under high subsonic speed conditions and the influence of shock wave on boundary layer flow under different Reynolds number conditions were mainly analyzed. The results showed that when the Reynolds number decreased under high subsonic speed conditions, the suction side boundary layer developed from no separation to a closed separation bubble, and finally to an open separation. In the absence of shock wave, the starting position of laminar separation was not greatly affected by isentropic outlet Mach number, which mainly affected the transition and reattachment position of the separation boundary layer. Shock laminar boundary layer interactions occurred on the suction surface of the blade under transonic conditions. The development of the boundary layer after interaction relied on the Reynold number and the strength of shock. The numerical results were in good agreement with the experimental results, but there were differences in the prediction of the pressure coefficient at very low Reynolds numbers.
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