轴流涡轮的初步设计及性能分析

Preliminary Design and Performance Analysis of Axial Turbine

增压器轴流涡轮快速高效的初步设计可以减短涡轮的设计周期,提升涡轮增压器效率。根据轴流涡轮的热力工作过程建立了合理的数学模型,以最小出口绝对马赫数为目标,对该数学模型进行了约束控制,结合损失模型开发了轴流涡轮的一维设计优化程序,得到涡轮机的几何参数,进行三维建模,整个过程极大地简化了轴流涡轮的设计建模流程,实现了单级增压轴流涡轮的高效设计。利用南京航空航天大学某微型轴流涡轮验证了程序设计与建模方法的可行性,得到性能曲线与文献值吻合较好,流量最大误差在±6.6%以内,总总效率最大误差为1.8%;并将该方法应用于NASA单级轴流涡轮的验证,在40%、70%、100%设计转速下的阻塞流量预测误差不超过1%,从而验证了设计计算程序与建模方法的准确性与可行性,同时显示出较好的预测效果。

The rapid and efficient preliminary design of the turbocharger axial turbine can shorten the design cycle of the turbine and improve the efficiency of the turbocharger.In this paper,a reasonable mathematical model is established based on the thermal working process of the axial turbine.The minimum exit absolute Mach number is taken as the goal,the mathematical model is constrained and controlled.The one-dimensional design optimization program of the axial turbine is developed in combination with the loss model.The geometric parameters of the turbine are modeled in three dimensions.The whole process greatly simplifies the design and modeling process of the axial turbine and realizes the efficient design of the single-stage supercharged axial turbine.The feasibility of the program design and modeling method was verified by using a micro axial turbine from Nanjing University of Aeronautics and Astronautics,the performance curve obtained was in good agreement with the literature value,the maximum error of flow is within±6.6%,and the maximum error of total efficiency is 1.8%.This method is applied to the verification of NASA single-stage axial turbine,and the prediction error of the blocking flow at 40%,70%,and 100%design speed is not more than 1%,which verifies the accuracy and feasibility of the calculation program and modeling method designed in this paper,at the same time showing a better forecasting effect.