摘要
对于进口相对马赫数较高的超音叶栅,合理组织激波结构是设计中的重要课题。为探索削弱激波损失的途径,建立不同激波结构的计算模型,计算得到了激波结构对叶栅性能的影响规律和特点。为设计性能良好的超音叶型,利用叶型参数化方法构造出中弧线为"S"型预压缩叶型,实现叶栅通道内预压缩及一道斜激波加一道正激波增压;利用优化软件对上述叶型进行优化,叶栅性能提升明显;优化结果显示,正激波位置对超音叶栅性能有较大的影响。
For supersonic cascade with high inlet relative Mach number, it is important to organize well the shock wave structure. To explore the method of weakening the shock loss, this paper discussed the in- fluences of different shock structures through three calculation models. In order to design a supersonic blade with good performance, the initial compressor blade with ＇ S＇ style mean cambers was generated. The su- personic cascade improves the static pressure through an oblique shock and a normal shock wave structure. Then, this paper adopted the optimization software to optimize the initial blade profile. The aerodynamic performance of optimized cascade performance was improved obviously. The optimization results also show that the position of normal shock wave has a great influence on the cascade performance.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2013年第8期1050-1055,共6页
Journal of Propulsion Technology
关键词
超音叶栅
激波结构
叶型参数化
优化设计
Supersonic cascade
Shock structure
Airfoil parameterization
Optimization design
