The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade
The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade
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DOI：
10.3390/aerospace9110713
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发表时间：
2022-11
期刊：
影响因子：
2.6
通讯作者：
Yinxin Zhu;Zhen-bing Luo;Wen-qiang Peng;Qiang Liu;Yan Zhou;Wei Xie;Pan Cheng;Zhengxue Ma;Xuzhen Xie
中科院分区：
文献类型：
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作者：
Yinxin Zhu;Zhen-bing Luo;Wen-qiang Peng;Qiang Liu;Yan Zhou;Wei Xie;Pan Cheng;Zhengxue Ma;Xuzhen Xie
为了有效降低高背压下超声速叶栅尾缘激波损失，提出了一种基于空气射流的激波控制方法。空气射流布置在叶片的压力侧，在后缘激波的上游。通过计算分析了流动控制机理及各参数的影响。结果表明，空气射流在叶栅通道内形成斜激波，对气流产生减速和增压作用。由此产生的膨胀波下游的喷气槽的后缘激波的强度减弱。这可以有效地将正激波转化为斜激波，从而减弱激波损失。当射流与通道气流的质量流量比为0.35-1.11%，射流槽距后缘激波根部的距离约为边界层厚度的5倍时，控制效果最佳。该方法可以降低超声速叶栅的总压损失，与无控制状态相比，最大改善效果可达7.29%。
To effectively reduce shock wave loss at the trailing edge of a supersonic cascade under high back-pressure, a shock wave control method based on air jets is proposed. The air jet was arranged on the pressure side of the blade in the upstream of the trailing-edge shock. The flow control mechanism and effects of parameters were analyzed by computational methods. The results show that the air jet formed an oblique shock wave in the cascade passage which decelerated and pressurized the airflow. The resulting expansion wave downstream of the jet slot weakened the strength of the trailing-edge shock. This could effectively change the normal shock into oblique shock and thus weaken the shock loss. Optimal control effect was achieved when the mass flow rate ratio of the jet to the passage airflow remained 0.35–1.11% and the distance from the jet slot to the shock foot of the trailing-edge shock was about five times the thickness of the boundary layer. The proposed method can reduce the total pressure loss of a supersonic cascade, with the maximum improvement effect reaching 7.29% compared to the no-control state.