航空发动机尾喷管射流对道面影响数值仿真  

The Numerical Simulation of Nozzle Jet Flow Effect on Runway Surface

作　　者：史亚锋 SHI Yafeng(Zhongyuan-Petersburg Aviation College,Zhongyuan University of Technology,Zhengzhou 450000,China)

机构地区：[1]中原工学院中原彼得堡航空学院,河南郑州450000

出　　处：《郑州航空工业管理学院学报》2024年第3期26-29,38,共5页Journal of Zhengzhou University of Aeronautics

摘　　要：采用有限元方法对某型发动机尾喷管射流场在全加力工作状态下进行了定常数值模拟,并将数值计算结果与实验数据进行对比,验证了本文采用的计算方法和湍流模型的正确性。对不同尾喷管射流角度对道面的影响进行了定常数值模拟,计算结果表明尾喷管射流对道面具有强烈的冲击作用,表现为气流作用在道面上极高的温度和速度。The jet flow field of aero-engine nozzle at the full afterburner state is simulated by finite element method.The computation results agrees well with the experiment data,which proves the correctness of computation method and turbulence model.The flow fields with three different angels of nozzle jet flow to the runway surface are simulated.The simulation results show the jet flow with high velocity and temperature has a strong effect on runway surface.

关 键 词：尾喷管 射流 温度 速度 数值模拟 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]