摘要
在高空、低速、低雷诺数下,进行具有较强抗分离能力的新叶型研究,探索叶型设计的新概念和新方法,并发展相应的低雷诺数压气机叶片二维设计技术是十分关键的。本文进行了低雷诺数条件下二维压气机叶栅流场计算与对比,在探索高空、低速、低雷诺数对压气机叶型性能影响的基础上,以发展适应低雷诺数流动的、具有较强抗分离能力的新叶型为最终目标,进行叶型设计新理论和新方法的探索,为最终突破低雷诺数下叶型设计的关键技术提供了可行的途径,并为三维叶片优化造型打下了基础。
New profile design technique, which could prevent strong separation under high altitude, low speed and low Reynolds number conditions, should be investigated. Some new design idea and two dimensional design procedure have been discussed. Calculation and comparison results were presented in this paper for two dimensional compressor cascade under low Reynolds number. The effects of high altitude, low speed and low Reynolds number on profile performance were discussed to develop new profile which will keep satisfactory flow field to prevent strong separation. The purpose of this research is to provide useful procedure for 2d profile and setup basis for three dimensional blade design.
出处
《燃气涡轮试验与研究》
2007年第4期1-6,共6页
Gas Turbine Experiment and Research
关键词
风扇/压气机
低雷诺数
叶型设计
流场计算
fan/compressor
low Reynolds number
profile design
flow field calculation
