摘要
为了分析超音速叶型关键几何参数的敏感性,以NASA Rotor67跨音速压气机转子为研究对象,采用准二维的数值方法,研究弯度、最大厚度位置等叶型关键几何参数的变化对跨音速压气机转子顶部叶栅激波结构及流场性能的影响.结果表明,与最大厚度位置相比,叶型弯度的影响更为显著;以安装角表征叶型弯度,在63°～65°范围内存在最优值使总压比达到最大.
To analyse the sensitivity of critical geometry parameters in a supersonic aerofoil, a transonic rotor, NASA Rotor67, is selected as the baseline rotor. By adopting the quasi -2D simulation methods, this paper investigates the influence of the critical geometry parameters such as the camber angle and location of maximum thickness on the shock structure and aerodynamic performance. The results indicate that the camber angle has a more remarkable effect than the location of maximum thickness. In addition, there exists an optimum stagger angle, representative of the camber angle, between 63 and 65 degrees resulting in the largest total pressure ratio.
出处
《节能技术》
CAS
2014年第6期483-486,共4页
Energy Conservation Technology
基金
上海交通大学"新进青年教师启动计划"(12X100040080)
高等学校博士学科点专项科研基金(20130073120101)
关键词
跨音速压气机
超音速叶型
关键几何参数
激波结构
流场性能
transonic compressor
supersonic aerofoil
critical geometry parameters
shock structure
aerodynamic performance
