为了探究舰载机起飞时发动机尾喷流撞击偏流板( Jet Blast Deflector,JBD)后反射回流对进气道温升的影响,以模型机和喷气偏流板为研究对象,通过求解三维雷诺平均纳维-斯托克斯方程和Menter SST湍流模型方程,对舰载机准备起飞时的飞机内、外流场进行了数值模拟。利用线积分卷积方法对流场进行了可视化显示,分别研究了JBD不同倾角以及不同环境风速情况下,喷流回流对进气道温升的影响。计算结果表明：环境风速保持不变,在JBD倾角由30°逐步增大到60°的过程中,进气道出口截面面平均温升(ΔTav )总体呈增大趋势,当倾角由45°变为50°,进气道出口截面面平均温升陡增；对于特定的JBD倾角,在环境风速逐步增大过程中,存在一个临界风速,当风速小于临界风速时,进气道出口截面ΔTav随风速增加而增大。当风速大于临界风速时,进气道出口截面ΔTav随风速增加而显著降低。计算结果对于偏流板布局选择具有一定的指导意义。%To analysis the influence of jet blast deflector ( JBD) backflow on inlet temperature when the carrier-based aircraft is to take off,the three dimensional Reynolds averaged Navier-Stokes equations and Menter SST turbulent model equations were solved to simulating the external and internal flow around a model plane and the jet blast deflector. The line integral convolution method was applied to visualize the flow. The inlet performance varying pattern was obtained under the condition of different JBD deflection angles and different ambient wind velocities. The results show that face-average temperature rise (ΔTav ) of inlet/engine interface plane increases when the JBD deflection angle turns form 30 ° to 60 ° , and the face-average temperature rises abruptly when the JBD deflection angle turns form 45 ° to 50 °;For a given JBD deflection angle,there is a critical wind velocity. When the speed of wind is lower than the critical velocity,ΔTav increases along with the increase of wind speed. However,when the speed of wind is higher than the critical velocity,the ΔTav decreases along with the increase of wind speed. This result can show some guidelines to the layout of the jet blast deflector.
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