中文摘要：

为验证缝前端不同径向偏转的机匣处理的扩稳效果,通过定常与非定常数值研究的方法,以工作于设计转速下的rotor 67为载体,研究机匣处理对rotor 67稳定性的作用.详细地分析各工况下它们对叶顶流场、间隙泄漏流和叶顶激波的影响,确定它们对压气机稳定性的作用机理.研究发现：实壁机匣近失速工况时rotor 67发生了叶尖堵塞型失速;3种缝式机匣处理都能进行有效的扩稳,其中缝前段逆旋转方向偏转的CTP45机匣处理提高了转子的综合失速裕度27%,实壁机匣近失速工况下降低了转子效率0.98%,但提高了通过转子气流的压比,它有效地抑制了转子叶片压力面前缘的阻塞气流团,获得了最好的扩稳效果.随着流量的减小,压比的增加幅度更加明显.

英文摘要：

In order to verify the effect of stability intensification with casing treatment through radial off- sets of slot front, the stationary and nonstationary numerical investigation methods were employed and the rotor 67 with design speed was＇ taken as carrier to investigate and compare emphatically the effect of casing treatment on stability of the rotor 67. Their influence on the flowfield at blade tip, leakage flow through slot, and shock wave at blade tip in detail under various conditions, and to determine their functioning mechanism for stabilizing the compressor. It was found by the investigation that within the rotor 67 with solid untreated casing wall, blade tip blockage stall would take place in condition of near-stall flow. All the three casing treatments could effectively perform the stability intensification, among-them the CTP45 slot with anti-rotating offset of front slot segment could make SMI （stall margin improvement） increase by 27% ,while its efficiency decrease by 0.98% in near-stall condition for solid wall and the pressure ratio of the gas flow across the rotor increase, so that the gas-flow blocking front edge of blade pressure side would effectively be constrained and the best result of stability intensification obtained. Along with the decrease of flow, the increase amplitude of the pressure ratio would be even more remarkable.