自循环机匣处理周向覆盖比例和喷嘴轴向位置对轴流压气机扩稳效果的影响  

Effects of Circumferential Coverage Ratio and Axial Positionof Injector on Axial Compressor Stability Enhancementwith Self-Recirculating Casing Treatment

作　　者：王广 楚武利[1,2] 迟志东 陈向艺 张皓光 WANG Guang;CHU Wu-li;CHI Zhi-dong;CHEN Xiang-yi;ZHANG Hao-guang(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Collaborative Innovation Center of Advanced Aero-Engine,Beijing 100191,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710129 [2]先进航空发动机协同创新中心,北京100191

出　　处：《推进技术》2020年第6期1237-1249,共13页Journal of Propulsion Technology

基　　金：国家自然科学基金(51576162);国家自然科学基金重点项目(51536006)。

摘　　要：为了揭示自循环机匣处理周向覆盖比例和喷嘴轴向位置对扩稳效果的影响规律,在固定引气位置于叶顶阻塞区域的前提下,设计了6个不同周向覆盖比例和4个不同喷嘴轴向位置的自循环机匣处理结构,并以一个高亚声速轴流压气机转子为研究对象进行了数值模拟。结果表明:随着周向覆盖比例增大,压气机的综合稳定裕度先增大后减小,峰值效率则单调降低,综合稳定裕度改进量最大的周向覆盖比例为90%,兼顾扩稳效果和效率损失的最佳周向覆盖比例为30%。随着喷嘴位置由叶顶前缘沿轴向逐渐前移,压气机的扩稳效果变化不大,但效率有所提升,而且喷嘴位置越往前移,效率提升越多。In order to reveal the effects of the circumferential coverage ratio and the axial position of the injector of self-recirculation casing treatment on axial compressor stability enhancement,the self-recirculation casing treatment structures of six different circumferential coverage ratios and four different axial positions of injector were designed under the premise of the fixed bleed air position in the top blocking area.Then,a high subsonic axial compressor rotor was selected as the research object for numerical simulation.The results show that with the increase of circumferential coverage ratio,the comprehensive stability margin of the compressor increases first and then decreases,the peak efficiency decreases monotonously.The maximum coverage ratio of the comprehensive stability margin is 90%,and the optimal circumferential coverage ratio for both the compressor stability enhancement effect and the efficiency loss is 30%.As the injector axial position is gradually moved forward from the leading edge of the blade tip,the comprehensive stability margin of the compressor does not change much,but the efficiency is improved,and the more the injector position moves forward,the more the efficiency is improved.

关 键 词：轴流压气机 自循环机匣处理 周向覆盖比例 喷嘴轴向位置 扩稳机理 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]