进气温度畸变对多级跨声速压气机气动性能影响的试验研究  

Experimental investigation on the influence of intake temperature distortion on the aerodynamic performance of multi-stage transonic compressor

作　　者：吴亚东[1] 朱自环 明乐乐 WU Yadong;ZHU Zihuan;MING Lele(School of Mechanical Engineering,Shanghai Jiao Tong University,Shanghai 200240,China)

机构地区：[1]上海交通大学机械与动力工程学院,上海2000240

出　　处：《燃气涡轮试验与研究》2024年第4期11-17,共7页Gas Turbine Experiment and Research

基　　金：航空发动机及燃气轮机基础研究项目(J2019-II-0004-0024);航空发动机及燃气轮机基础科学中心项目(P2022-B-V-004-001)。

摘　　要：进气温度畸变是严重影响压气机气动稳定性的一个重要因素。设计了一种进气电加热畸变发生器,以4级跨声速压气机试验件为研究对象,开展了不同转速下的压气机进气温度畸变气动性能测试试验。结果表明,进气温度畸变使跨声速压气机特性线向小流量工况偏移,且转速越高,偏移量越大;温度畸变导致总压比和等熵效率显著降低,其中总压比最大降幅为4.2%,等熵效率最大降幅为14.7%。高转速下畸变工况导致机组振动超限,说明进气温度畸变产生的不均匀热负荷对压气机的稳定安全运行产生了负面影响。当电加热段功率固定时,由于进气量随着转速增加而增加,高温区与低温区温差减小,进气总温畸变强度降低。Intake temperature distortion is one of the critical factors significantly affecting the aerodynamic stability of compressors.An intake electric heating distortion generator was designed,and a four-stage transonic compressor was used as the test subject.Aerodynamic performance tests were conducted under intake temperature distortion at various rotational speeds.The results show that intake temperature distortion causes the characteristic lines of the transonic compressor to shift towards lower flow conditions,with a greater offset at higher speeds.Simultaneously,temperature distortion leads to a significant decrease in pressure ratio and isentropic efficiency,with a maximum decrease in pressure ratio of 4.2%and an isentropic efficiency reduction up to 14.7%.Under high rotating speed conditions,distortion-induced vibrations exceed limits,indicating that uneven thermal loads caused by inlet temperature distortion have a negative impact on the stable and safe operation of the compressor.When the power of the electric heating section is fixed,the intake air mass flow increases with the increase in speed,resulting in a decrease in the temperature difference between the high-temperature and low-temperature regions and a reduction in the intensity of the total temperature distortion of the intake air.

关 键 词：航空发动机 进气温度畸变 多级跨声速压气机 气动性能 试验研究 电加热 

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]