S型进气道沿程结冰参数变化的数值模拟  

Numerical simulation of icing parameters along S-shaped intake

作　　者：胡娅萍[1] 庞黎刚[1,2] 吉洪湖[1] 曹广州[1] 冯晓星[1,2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空工业集团公司商用航空发动机有限责任公司,上海201108

出　　处：《航空动力学报》2014年第1期23-30,共8页Journal of Aerospace Power

摘　　要：采用欧拉-欧拉法,对低来流马赫数和大气结冰条件下S型进气道沿程的空气-过冷水滴两相流场进行了数值计算,获得了进气道沿程和出口面上结冰参数的分布和变化特征.计算结果表明:当来流马赫数从0.1增加到0.5时,进气道入口处附近相对于来流的气动降温从6K增大到17K左右,进气道出口面上的温度畸变指数逐渐增大,液态水含量畸变指数先急剧增大后缓慢减小,在研究范围内来流马赫数为0.2时液态水含量畸变值达到最大.Under atmospheric icing conditions and at low incoming flow Mach number, a two-phase flow field of air and super-cooled water droplets along S-shaped intake was numerically simulated with the Euler-Euler method. The distributions of the icing parameters along the S-shaped intake and on the outlet surface were studied. The results show that with the increase of incoming flow Maeh number from 0.1 to 0.5, air temperature drop relative to the incoming flow near the entrance increases from 6 K to about 17 K; the distortion index of temperature on the outlet increases gradually, while the distortion index of liquid water content increases rapidly at first and then decreases slowly with the maximum value at incoming flow Mach number of 0.2.

关 键 词：S型进气道 结冰参数 两相流 数值模拟 畸变指数 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]