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随着高空无人飞行器研究的不断升温,高空低雷诺数条件下动力装置的研究越来越受到人们的重视.结合近年来国内外相关领域的研究工作,对低雷诺数低压涡轮内部复杂流动机理的研究进展进行了介绍,包括低雷诺数情况下低压涡轮内部非定常流动的特点,叶片边界层分离及转捩现象机理,上游周期性尾迹与下游叶片边界层相互作用机理等.在此基础上给出了适合低雷诺数条件的低压涡轮气动设计方法:尾迹通过与边界层的相互作用,能够抑制分离,进而减小叶型损失,在气动设计中有效引入非定常效应可以大幅度提高低压涡轮的气动负荷或降低气动损失,最终达到提高性能的目的;数值及实验结果验证了这种设计方法的有效性.
With the research on the UAV at high altitude, the research on the power plant under high altitude and low Reynolds number conditions has drawn more and more attention.Based on the researches in related fields both at home and abroad in recent years, the complex flow mechanism in low Reynolds number low pressure turbine Including the characteristics of unsteady flow in low-pressure turbine under low Reynolds number, the mechanism of the separation and transition of the boundary layer of the blade, the interaction mechanism between the upstream periodic wake and the downstream vane boundary layer, etc. On the basis of this, The aerodynamic design method for low pressure turbine with low Reynolds number is given. The interaction of the wake with the boundary layer can suppress the separation and reduce the loss of the vane. The introduction of unsteady effect into the aerodynamic design can greatly improve the low pressure turbine Of the aerodynamic load or reduce the aerodynamic losses, and ultimately achieve the purpose of improving performance; numerical and experimental results verify the effectiveness of this design method.