沈阳航空航天大学学报2025，Vol.42Issue(1)：45-56,12.DOI:10.3969/j.issn.2095-1248.2025.01.005
非均匀转子叶顶间隙改型对单级压气机流场结构的影响
Influence of the non-uniform rotor tip clearance modification in single-stage compressor flow structure
摘要
Abstract
In order to reduce the flow loss at the tip clearance of rotor,the shape of rotor tip clearance was optimized with NASA stage 35 as the research object.The effect mechanism of different rotor tip clearance shapes on single-stage compressor performance and flow field structure was studied by numerical simulation.The results show that the stability margin increases greatly with the decrease of tip clearance value,parallel-type tip clearance,hump-type tip clearance and concave-type tip clearance increase by 2.21%,2.30%and 2.54%respectively,and peak efficiency is almost constant.After the modification the total pressure ratio is increased,and high entropy generation area in the leading edge of the rotor is reduced.The inter-action between shock wave and tip leakage flow is weakened,the leading edge spillage phenomenon is suppressed,the high vorticity area in the rotor channel is reduced,the rotor channel blockage phenomenon is weakened,and the total pressure loss coefficient in the stator channel is reduced.After the modification the rotor stall mechanism changes.The rotor stall may be caused by tip leakage vortex breaking near the rotor pressure surface,large boundary layer separation area on the suction surface,and spanwise underflow accumulation in the corner region of the shroud.关键词
间隙改型/叶尖泄漏流/激波/前缘溢流/单级压气机/叶顶间隙Key words
clearance modification/tip leakage flow/shock wave/leading edge spillage/single-stage compressor/tip clearance引用本文复制引用
于瀚科,张国臣,孙丹,徐志晖..非均匀转子叶顶间隙改型对单级压气机流场结构的影响[J].沈阳航空航天大学学报,2025,42(1):45-56,12.基金项目
翼型、叶栅空气动力学重点实验室基金(项目编号:614220121050125). （项目编号:614220121050125）
