摘要
针对总压比20以上的某10级轴流压气机,使用一维无反射和通量守恒两类转静交界面模型进行单通道定常数值仿真,并与试验结果对比,从交界面的守恒和无反射两方面特性分析对计算结果的影响及其机理。结果表明:一维无反射交界面可有效消除激波反射,但无法保证交界面守恒性;对于本文研究对象,设计点流量、峰值效率和最高压比分别偏高5%、2.6%和4%;转静交界面通量不守恒导致的误差,会随着级数增加而累加。通量守恒交界面虽然存在激波反射等误差,但仍可求出与试验形状接近的性能曲线,除流量偏高3%,其余主要指标均与试验吻合。因此,计算中需综合考虑压气机的级数、负荷水平和反动度、叶尖间隙、激波的形状和强度、超跨音叶片前缘与交界面的距离,以选择合适的交界面模型。
One dimensional non-reflection and flux conservation rotor-stator interface models were taken to comparison by using single-passage steady-state computational fluid dynamics(CFD)simulation in a 10-stage axial compressor with pressure ratio over 20.Results were also compared by experimental datas,to analyze the differences between these two rotor-stator interface models in simulation and reveal their mechanism.The result shows that one dimensional non-reflection interface can effectively diminish reflection of shock waves but cannot maintain conservation.For the compressor studied in this paper,the mass flow rate,peak efficiency and maximum pressure ratio are over estimated by 5%,2.6%,and 4%respectively.Meanwhile,the error brought by non-conservation will accumulate when stage number increases.Although flux conservation interface cannot diminish wave reflection,it still gets performance curves that close to experimental data.Except for mass flow rate is over estimated by 3%,other parameters are consistent with experiment.During simulation,the number of stages,the load and reaction,tip clearance,the intensity and shape of shock wave,and the distance between the leading edge of the supersonic blade and the rotor-stator interface should be comprehensively considered to select the appropriate interface model.
作者
刘天一
曹传军
Liu Tianyi;Cao Chuanjun(AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,China)
出处
《燃气轮机技术》
2023年第2期19-26,共8页
Gas Turbine Technology
关键词
多级轴流压气机
数值仿真
通量守恒
无反射
multistage axial compressor
numerical simulation
flux conservation
non-reflection
