摘要
通过数值模拟对具有51°叶型折转角的环形扩压叶栅进行了研究.将外流飞行器上控制附面层流动的基本思想和修型措施应用于弯叶片的局部修型,结合近壁面附面层流动和总压损失对比分析了大折转角扩压叶栅采用直叶片、弯叶片和局部修型弯叶片的气动性能.结果表明:在大折转角、高亚声速气流进口条件下,局部修型弯叶片能更有效的控制大逆压梯度下叶栅内附面层的发展,提高叶栅气动性能.
This paper presents a numerical study of a high-turning angle compressor stator with 51°. The main ideas and local modification to achieve better control of boundary layer flow in aircraft are applied to the contouring of bowed stator. The skin friction line of suction side and total pressure loss are discussed in the straight blade, bowed blade and local modified bowed blade. The results show that the local modified bowed blade can effectively control the boundary layer flow and it is applicable to the boundary conditions of high ad- verse pressure gradient, high-turning and high subsonic inlet velocity.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第3期465-470,共6页
Journal of Aerospace Power
基金
国家自然科学基金重点项目资助(50236020)
关键词
航空
航天推进系统
大折转角
局部修型
扩压叶栅
弯叶片
aerospace propulsion system
high-turning angle
local modification
compressor stator
bowed blade
