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本文采用数值模拟方法捕捉到了不同位置周向单槽对某低速压气机稳定性裕度的影响规律并分析其原因。结果表明:周向槽位于叶片前缘附近扩稳效果差,位于叶顶弦长中下游区域扩稳效果好。采用机匣壁面剪切应力定量识别泄漏流与主流交界面的轴向位置,发现交界面在节流过程中主要存在两种移动规律,并由此将所研究的周向槽分为准模态和突尖两类周向槽。对于突尖类周向槽机匣,交界面的位置取决于叶顶间隙流体的轴向动量平衡。周向槽可以削弱与主流相抗衡的流体的轴向动量,这种削弱作用越强,周向槽机匣的扩稳效果越好。
In this paper, the numerical simulation method is used to capture the effect of single slots in different positions on the stability margin of a low-speed compressor and the reasons are analyzed. The results show that the circumferential groove located near the leading edge of the blade has poor stabilizing effect and the stabilizing effect located in the middle and downstream of the chord length. Using the casing wall shear stress to quantitatively identify the axial position of the leakage flow and the main interface, it is found that there are mainly two kinds of movement laws at the interface, and the circumferential grooves studied are divided into quasi-modal And sudden sharp two types of circumferential groove. For the tip-notch circumferential groove casing, the location of the interface depends on the axial momentum balance of the tip clearance fluid. The circumferential groove can weaken the axial momentum of the fluid which is counter-current to the mainstream, and the stronger this weakening effect is, the better the stability of the circumferential groove casing will be.