轴流压气机特性计算及激波模型研究

Study on Performance Simulation and Shock Model for Axial-Flow Compressor

为快速准确预估轴流压气机特性和激波损失,基于轴流压气机S2流面流线曲率法,分别采用正激波模型和改进的双激波模型,对某型2级跨声速风扇特性进行数值模拟计算,得到了100%设计转速近设计点与99.76%设计转速近堵塞点的总体性能和气动参数,以及95%、100%和110%设计转速的特性曲线。通过将计算结果与试验数据进行对比,分析研究了各激波损失模型在激波损失预估和风扇/压气机特性计算方面的差异。分析结果表明:在跨声速风扇/压气机近设计点激波损失和特性参数的计算中,正激波模型损失径向分布计算结果接近试验值,总压比和总效率计算值分别较试验值约低1.96%和2.54%,模型能够满足工程需要。而在近堵塞点,改进的双激波模型总损失计算值更接近试验值,总压比计算值和试验值很吻合,总效率计算值比试验值约高7.28%。改进双激波模型的不同转速线效率特性曲线也明显更接近试验值,模型能够较准确地预测远离设计点激波损失和特性参数。

In order to quickly and accurately predict performance and shock loss for axial-compressor, based on axial-flow compressor S2 flow surface streamline curvature method, simulation of the performance of a two-stage transonic fan was performed involving normal shock model and improved dual-shock model. Thus the overall performance and aerodynamic parameters on near-design and near-choke point, separately at 100% and 99.76% design rotation speed, and characteristic curves at 95%, 110%, and 110% design speed were obtained. The differences in prediction of shock loss and calculation of fan/compressor performance between the two shock loss models have been analyzed by comparing the simulation results and experiment data. The results show that on the near-design point, with the normal shock model, calculation result of radial distribution of loss is close to test result, and results of total pressure ratio and total efficiency are proximately lower than test result by 1.96% and 2.54% separately. Thus, the normal shock model can satisfy engineering need. While on the near-choke point, with improved dual-shock shock model, calculation result of total loss is closer to test result, result of total pressure ratio is consistent with test result, and result of total efficiency is about 7.28% higher than test result. And calculated characteristic curves are more similar to test curves. Therefore the use of improved dual-shock loss model can provide a more accurate calculation of shock loss and performance parameters on far off-design point.