随着现代高负荷航空发动机推重比的不断提高，风扇/压气机流动稳定性问题日益突出，而机匣处理是目前最有效的扩稳技术措施之一。本文首先回顾了机匣处理扩稳设计的研究历程和所面临的技术困难，进而阐述了SPS机匣处理（Stall precursor-suppressed casing treatment）的研究思路和基本原理。基于所发展的SPS机匣处理理论设计模型针对亚音风扇和跨音压气机进行了扩稳效果评估，结果显示，可以使亚音风扇和跨音压气机的流量裕度分别提高7.6%和6.8%。然后通过实验验证了SPS机匣处理的有效性，分别提高亚音风扇和跨音压气机流量裕度5.5%和9.3%，综合失速裕度均能够达到12%以上。同时，SPS机匣处理在小穿孔率大背腔情况下能够保持压气机原有的压升特性、峰值效率以及叶片径向负荷分布。最后，通过对失速先兆演化过程的对比分析发现，SPS机匣处理基于波涡相互作用改变了动力系统的阻抗边界条件，抑制了流场中的失速先兆的非线性放大，从而抑制旋转失速的发生。明显有别于传统机匣处理力图改变压气机尖区流动结构的扩稳思路，也完全不同于主动控制技术对消失速先兆波的研究策略，SPS机匣处理扩稳技术为风扇/压气机流动稳定性控制提供了一种可供选择的技术途径。

Modern aeroengine have been developed for high thrust to weight ratio, so the fan/compressor must support higher blade loading. Under this situation, it becomes more and more difficult to meet stall margin requirements. The casing treatment is one of the most effective ways to enhance the stall margin. A kind of casing treatment, named as stall precursor-suppressed (SPS), has been developed recently. The stall inception model can be used to deter-mine the variation range of the stall margin improvement with the SPS casing treatment for both subsonic and transonic compressors. The model predicts that 7.6% and 6.8% of stall margin improvement (SMI) can be achieved in a subsonic fan TA36 and a transonic compressor J69 Stage, respectively. The effectiveness of the SPS casing treatment is investigated and the experimental results show that the SPS casing treatment can achieve 5.5% and 9.3% of the SMI in TA36 and J69 Stage, respectively. Due to the fact that the distributions of the total pressure ratio along the spanwise direction are kept the same as those of the solid wall casing at the same mass flow rate, the SPS casing treatments with a small open area ratio and large backchamber enhance the stall margin without a obvious efficiency loss and a change of the pressure-rise characteristics. Furthermore, the generation and the evolution of the stall inception waves are suppressed and the non-linear development of the stall process is delayed with the SPS casing treatment.