平开口式通风口的进气流量数值仿真

Numerical Simulation of Air Flow Rate of Flat Opening Vent

以电子控制器冷却管道为研究对象,通过计算流体力学(CFD)仿真方法,计算飞机不同状态下冷却管道流量,并与试飞数据对比,分析误差,调整模型和边界条件,直至可接受范围。进而,运用该方法,建立大涵道比涡扇发动机平开口式通风口的模型,计算高度、速度、迎角、侧滑角等飞行状态条件下,通风口进气流量随参数的变化规律。结果表明,高度和速度参数对通风口进气流量影响很大:相同速度下,通风口进气总流量随高度的增加而减小;相同高度下,通风口进气总流量随速度的增加而增加;迎角和侧滑角对通风口进气总流量影响较小,迎角从负迎角增加到正迎角,进入短舱内部的冷却气流流量呈现先升高后降低的现象,在迎角0°附近达到峰值;侧滑角的变化对通风口进气流量影响不大。

Taking the electronic controller cooling pipeline as the research object,the cooling pipeline flow rate in different states of the aircraft was calculated by CFD simulation method,and compared with the flight test data.The error was analyzed and the model and boundary conditions were adjusted until the acceptable range.Furthermore, the model of the flat-opening vent of the large bypass ratio was established by using the above method and flat opening vent flow rate under the flight parameters such as altitude,speed,angle of attack and sideslip angle was calculated.The results show that the height and speed parameters have a great influence on the vent flow.At the same speed,the total flow of the vent decreases with the increase of the height;at the same height,the total flow of the vent increases with the increase of the speed.The angle of attack and the sideslip angle have little effect on the total flow of the vent.When the angle of attack increase from the negative to positive,and the flow of cooling airflow into the nacelle increase first and then decreases.It reaches the peak near the angle of attack of 0°.The variation of sideslip angle has little influence on the overall flow rate.