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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 predict the characteristics of axial flow compressor and the shock loss quickly and accurately, based on the flow curvature method of the S2 flow surface of the axial compressor, the positive shock wave model and the improved double shock wave model were used respectively to simulate a certain type of 2-stage transonic fan The overall performance and aerodynamic parameters of 100% design speed near design point and 99.76% design speed near plug point are obtained. The characteristic curves of 95%, 100% and 110% design speed are obtained. By comparing the calculated results with the experimental data, the differences between the shock loss models and the fan / compressor characteristics are analyzed and studied. The results show that the calculated radial shock loss of the normal shock model is close to the experimental value and the total pressure ratio and total efficiency are respectively calculated from the experimental values About 1.96% and 2.54% lower, the model can meet the needs of the project. At the near-clogging point, the calculated total loss of the improved double-shock model is closer to the experimental value. The calculated value of the total pressure ratio agrees well with the experimental value, and the calculated total efficiency is about 7.28% higher than the experimental value. The different rotational speed efficiency curves of the improved double shock model are also significantly closer to the experimental values, and the model can predict the shock loss and characteristic parameters away from the design point more accurately.