非均匀转子叶顶间隙改型对单级压气机流场结构的影响

于瀚科; 张国臣; 孙丹; 徐志晖

doi:10.3969/j.issn.2095-1248.2025.01.005

沈阳航空航天大学学报 ›› 2025, Vol. 42 ›› Issue (1) : 45 -56. DOI: 10.3969/j.issn.2095-1248.2025.01.005

航空宇航工程

非均匀转子叶顶间隙改型对单级压气机流场结构的影响

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Influence of the non-uniform rotor tip clearance modification in single-stage compressor flow structure

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摘要

为减弱转子叶顶间隙处的流动损失，以NASA Stage 35为研究对象，优化转子叶顶间隙形状。通过数值模拟研究不同转子叶顶间隙形状对单级压气机性能和流场结构的影响机理。结果表明，叶顶间隙值减小后，稳定裕度有较大提升，平行式小间隙、凹型间隙和凸型间隙分别增加2.21%、2.30%和2.54%，峰值效率几乎不变。改型后总压比提升，转子前缘区域的高熵增区面积减小。削弱激波与叶尖泄漏流相互作用程度，抑制前缘溢流现象，降低转子通道内高涡量区，减弱转子通道堵塞现象，静子通道内总压损失系数降低。改型后转子失速机制发生变化，转子失速可能是由转子压力面附近涡波破碎、吸力面较大的附面层分离及径向潜流在机匣角区聚集造成的。

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.