摘要
以某型涡扇发动机科研试飞为平台,设计搭建发动机附面层测量试验系统,进行了多种飞行工况及涡扇发动机工作状态下的附面层测量试验。通过试验数据分析和研究,评估了各计算参数对涡扇发动机进口附面层厚度的影响。建立三维数值模型,计算了相应工况下的附面层特性,计算数据与试验数据吻合良好。研究结果表明:随着发动机状态的增大,进气道出口的附面层物理厚度增大、附面层位移厚度减小,附面层对空气流通能力的影响降低。
Based on the flight test of a turbofan engine, the measure system of boundary layer were designed and built. Boundary layer of inlet was measured under different flight conditions and the engine conditions. By analyzing the test data, the effect of each calculating parameter on boundary layer thickness was evaluated. The model of numerical simulation for the boundary layer was established and modified using flight test data. By comparing the results of numerical simulation and flight test data, it was found the numer- ical results are in agreement with flight test data and the error can be acceptable. The results show that the thickness of boundary layer increases, displacement thickness of boundary layer and effect of boundary layer for mass flow reduces with the increasing of turbofan engine N1hs.
出处
《燃气涡轮试验与研究》
北大核心
2012年第3期54-57,62,共5页
Gas Turbine Experiment and Research
