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对单级跨声压气机Stage 35进行了单通道全三维定常数值模拟,开展了网格密度对计算结果影响的研究,从而确定了一套最佳网格配置,该套网格配置预测的总性能和基元性能与试验结果符合得最好.以此为基础对Stage 35的内部流场进行分析,发现其流动失稳最有可能是由动叶近叶顶靠近压力面侧的低能堵塞团引发的.随着流量的减小,间隙泄漏涡的强度和旋拧度随着叶片载荷的增加而增加,激波与泄漏涡相互干扰使得近失速条件下间隙泄漏涡破碎,涡破碎极有可能是动叶近叶顶靠近压力面侧低能流体产生的主要原因.
A one-pass full three-dimensional (3D) stationary numerical simulation of a single-stage transonic compressor Stage 35 was carried out to study the effect of grid density on the calculation results. A set of optimal grid configurations were then determined. The set of grid configurations predicted total Performance and elemental properties are in good agreement with the experimental results.On the basis of the analysis of the internal flow field of Stage 35, it is found that the flow instability is most likely caused by the low-energy plugging mass near the pressure side of the blade near the blade tip .With the decrease of flow rate, the strength and screwing degree of clearance leakage vortex increase with the increase of blade load. The mutual interference of shock wave and leakage vortex makes the gap leakage vortex broken under near-stall condition and the vortex crushing is very likely Is the main reason for the generation of low-energy fluid near the blade tip near the pressure side.