连续旋转爆震波与涡轮静子叶栅相互作用数值研究

Numerical Study on Interaction Between Continuous Rotating Detonation Wave and Turbine Stator Blades

关键词:  旋转爆震  涡轮静子叶栅  非定常  燃烧室  数值研究

Key words:  Rotating detonation  Turbine stator blade  Unsteady  Combustor  Numerical study

摘要:

为了研究旋转爆震燃烧与涡轮部件组合的工作特性，对旋转爆震波与涡轮静子叶栅的相互作用过程进行了数值模拟，考虑了不同传播方向的影响，详细分析了爆震波与涡轮叶栅相互作用机理。结果表明，爆震波顺着叶盆方向传播时，在叶栅的叶盆处出现高温区，逆向传播时，同时在叶盆和叶背处都出现高温区；并且顺向传播时产生的反射波强度更大。分析了涡轮进出口压力和温度的变化过程，发现涡轮对压力的波动有一定抑制作用，顺向和逆向传播的爆震波经过涡轮叶栅后压力变化幅值分别下降了68%和57%。得到了对于当前叶栅构型，顺向传播的爆震波总压损失为11.03%，而逆向传播的爆震波总压损失为6.7%。

Abstract:

To investigate the operating characteristics of rotating detonation combustion and turbine， the interaction between the rotating detonation wave propagation and the turbine stator blade was numerically simulated. Considering the influence of different propagation directions， the interaction mechanism between detonation wave and turbine blade was analyzed in detail. The results show that when the detonation wave propagates along the blade basin direction， there is a high temperature region appearing on the blade basin while there is a high temperature region appearing at both the blade basin and the back of the blade for the backward propagating. The reflected wave intensity is greater when the detonation wave propagates along the blade basin direction. The pressure and temperature variation process with time of flow before and after turbine were analyzed. It is found that the pressure fluctuation has been weakened after propagating through the turbine. The amplitude of pressure oscillation decreases by 68% and 57% respectively for the detonation wave forward and backward propagation .For the current blade configuration， the total pressure loss of forward propagation is 11.03%， while that of backward propagation is 6.7%.