玄云SW120B航空发动机尾流热流场数值分析

Numerical analysis of wake thermal flow field for SW120B aero-engine

以玄云SW120B航空发动机为研究对象,在纯气相作用和发动机慢车状态下,对尾部热流场进行建模和数值模拟,通过分析尾部温度场和流场特性,得到温度和流速的分布及变化规律。在喷口端面中心建立坐标系,研究结果显示:尾流出口处热流的温度和流速呈三维锥体分布,以喷口为中心向外扩散,流体远离喷口0.6 m处开始呈现偏离中心轴向的趋势。尾流高温区域为:z<0.9 m,y<0.5 m,温度范围为569~976 K。低温区域为:z>2.5 m,y>0.6 m,最高温度不超过323 K。尾流高流速区域为:z<0.2 m,y<0.2 m,流速范围为77~100 m/s。低流速区域为:z>0.9 m,y>0.2 m,最高流速不超过20 m/s。人体安全区距离为:z>2.5 m,y>0.5 m。研究方法可为大型民航发动机尾流热流场分析和发动机慢车下的地面除冰作业安全区域划分提供参考。

This paper takes Xuanyun SW120B aero-engine as the research object.The thermal flow field of the tail is modeled and numerically simulated under the pure gas-phase action and engine deceleration state.By analyzing the characteristics of the tail temperature field and flow field,the distribution and change rule of the engine tail jet flow field and temperature field are derived.A coordinate system is established at the center of the nozzle end face and our results show the temperature and flow rate of the heat flow at the exit of the tail flow is a three-dimensional cone distribution,with the nozzle as the center of the outward diffusion.The fluid is away from the nozzle 0.6 m at the beginning of the tendency to deviate from the center of the axial direction.The high temperature region of the wake stream:z is less than 0.9 m,y is less than 0.5 m,and the temperature range is569~976 K.The low-temperature region:z is more than 2.5 m,y is more than 0.6 m,and the maximum temperature is not more than 323 K.The high-flow velocity region of the wake stream:z is less than 0.2 m,y is less than 0.2 m,and the flow velocity range is 77~100m/s.The low-flow velocity region:z is more than 0.9 m,y is more than 0.2 m,and the highest flow velocity does not exceed 20m/s.The distance of human safety zone:z is more than 2.5m,y is more than 0.5 m.Our research method may provide some references for analyzing the thermal flow field of the wake stream of a large civil aviation engine and dividing safety zone of the ground de-icing operation under the engine jogging.