叶顶微喷气提高旋转畸变条件下低速轴流压气机失稳裕度的机理分析

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基金项目: 中国博士后基金(20080430306);国家自然科学基金(50736007)

Experimental study of the mechanism of improving stall margin of low speed axial-flow compressor with micro-injection under rotating inlet distortion

1.
School of Jet and Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2.
China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou 412002, China
3.
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China

摘要: 对旋转畸变条件下轴流压气机的失稳特性进行了实验研究,结果表明,畸变影响区内叶顶泄漏流的前缘溢出造成了旋转失速的提前发生,缩减了压气机的失稳裕度.叶顶微喷气方法有效地提高了旋转畸变条件下轴流压气机的失稳裕度,其原因在于,实施叶顶微喷气后,临近失速时,压气机顶部畸变区诱发的分离团受到抑制,减少了其诱发旋转失速的可能性,从而实现扩稳目的.
- 旋转畸变 /
- 旋转失速 /
- 微喷气
Abstract: An experimental investigation was carried out in the paper to clarify the flow mechanism of how micro-injection improves the stall margin of a low speed axial-flow compressor under rotating inlet distortion.The results show that,in distorted sectors,the tip leakage flow is pushed forward to the leading edge;as the mass flow rate is decreased,tip leakage flow would spill out of the blade passage and trigger the rotating stall.Micro-injection can inhibit the formation of distortion disturbances and then delay the occurrence of rotating stall.
- rotating inlet distortion /
- rotating stall /
- micro-injection

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