机匣抽气对转子颤振不稳定性影响分析

Analysis of the Influence of Casing Pumping on Rotor Flutter Instability

转子叶片颤振不稳定性是轴向压气机安全性的主要威胁之一。本文以跨声速轴流风扇第一级转子Rotor67为研究对象,基于能量法采用单通道开缝式环状抽气方式,对不同机匣抽气位置和不同抽气量状态下转子工作特性及气动弹性稳定性变化规律进行数值模拟研究。结果表明:近叶片前缘、叶片中间及近叶片后缘位置抽气时,转子的峰值效率均分别平均下降2.77%、0.9%和1.5%,峰值总压比近似不变。近叶片前缘位置抽气时,叶片稳定度δ较未抽气状态平均上升0.0965,随着抽气量的增大逐渐略微下降;叶片中间位置抽气时,叶片稳定度δ较未抽气状态平均上升0.1059,随着抽气量的增大逐渐略微上升;近叶片后缘位置抽气时,叶片稳定度平均下降约0.0114,而且不具有随抽气量变化而变化的规律。

Rotor blade chatter instability is one of the main threats to the safety of axial compressors.In this paper,the first stage transonic axial flow fan rotor Rotor67 is taken as the research object.Based on the energy method,the single-channel open slit ring pumping method is adopted to conduct numerical simulation research on the rotor operating characteristics and aeroelastic stability changes under different pumping positions and different pumping states of the casing.The results show that the peak efficiency of the rotor decreases by 2.77%,0.9%and 1.5%,respectively,when the rotor is pumped near the leading edge,the middle of the blade and the trailing edge of the blade,and the total peak pressure ratio is approximately unchanged.When the air was pumped near the leading edge of the blade and the middle of the blade,the vane stabilityδincreased by 0.0965 and 0.1059 on average,respectively.With the increase of the air pumping,the vane stabilityδshowed opposite change law.When the air was pumped near the trailing edge of the blade,the blade stability decreased by about 0.0114 on average,and it did not change with the change of the amount of air pumped.