虽然叶顶间隙的存在保障了航空发动机压缩系统的结构安全性，但由此引发的间隙泄漏流动会对压气机叶尖流动特性和工作稳定性产生显著负面影响。团队前期提出一种基于周向渐扩型间隙结构的跨音压气机转子间隙泄漏流抑制新方法。该方法通过在转子叶顶间隙附近产生的诱导激波实现对超音速泄漏流的显著抑制效果。本文聚焦影响诱导激波抑制泄漏流实际效果的两个关键因素——激波强度和周向位置，进一步揭示了诱导激波特性与跨音转子叶尖流动特性和工作裕度的内在关联，并归纳了诱导激波对跨音转子工作特性的影响规律。结果表明：通过增强诱导激波并使其周向位置远离转子叶顶吸力面侧边缘（可通过调节周向渐扩型间隙结构的周向扩张比予以实现），均可强化其对超音速间隙泄漏流的实际抑制效果。随着间隙周向扩张比的单调增大，跨音转子的工作裕度呈现出三种显著不同的变化趋势。相对较小的间隙周向扩张比会直接导致转子叶顶超音速泄漏流加速膨胀不足，从而难以形成诱导激波，此时跨音转子叶尖流场由泄漏流引起的堵塞效应反而会增强并使得其工作裕度出现减小。相对过大的间隙周向扩张比则会导致诱导激波在转子叶顶诱发波后的泄漏流分离。该现象在削弱诱导激波强度的同时，还会使其周向位置向叶顶间隙内部移动，此时继续增加间隙周向扩张比不再产生工作裕度新的增加量。当且仅当叶顶间隙周向扩张比位于1.125~1.625的区间范围时，可实现跨音转子工作裕度的线性增加，且最大增量达到8.9%以上。

The presence of tip clearance not only ensures the structural safety of compression system in aero-engines, but also exerts significant negative impacts on internal flow stability due to the leakage flow. Previous studies by our team have shown that the induced shock resulting from the circumferentially diverging clearance structure has remarkable effect on suppressing leakage flow in transonic compressor rotors. Therefore, the inherent correlations between the characteristics of induced shock and leakage flow are further elucidated in this paper, and the influencing rules of induced shock wave on tip flow characteristic of transonic rotors are summarized as well. The results demonstrate that the enhancement of inhibitory effects on leakage flow and increase in the rotor’s stall margin can be achieved by both intensifying the induced shock wave and shifting its circumferential position away from the suction side edge of blade tip, which is possible by adjusting the circumferential expansion ratio of diverging clearance. The stall margin of the transonic rotor exhibits three distinct variations as the circumferential expansion ratio of the diverging clearance increases monotonically, and a maximum improvement of over 8.9% can be achieved through feature variations of the induced shock wave. The insufficient acceleration of the supersonic leakage jet flow over blade tip due to a smaller circumferential expansion ratio poses challenges in inducing a shock wave, resulting in an increased blockage effect and reduced stall margin of rotor. Meanwhile, excessive circumferential expansion ratio results in a pronounced adverse pressure gradient originating from the induced shock wave, leading to leakage flow separation at the blade tip and consequently weakening the intensity of induced shock waves while shifting its circumferential position towards the blade tip. As a result, further increasing the circumferential expansion ratio does not yield an enhanced rotor stall margin but instead exhibits a slight decreasing trend.