摘要
以NASA Rotor35为研究对象,应用数值模拟手段深入分析了该转子在近失速工况的流动特征,针对其叶片吸力面附面层分离和上端壁处严重的二次流动,对比研究了叶表抽吸和上端壁抽吸对该转子流场结构以及气动性能的影响。计算结果表明:两种抽吸形式均使压气机的压比和效率有所提高。叶表抽吸可有效控制叶片通道激波,减小叶片吸力面的分离区,其最佳位置位于通道激波之后附面层发展处,在最佳抽吸量时压比提高了1.85%,效率提高了8.53%。上端壁抽吸有效地改善了近端壁区域的进出口气流角,其最佳位置位于叶片近前缘处,在最佳抽吸量时压比提高了0 86%,效率提高了4 54%。
A numerical simulation has performed to study the flow structure of the NASA Rotor35 in the near stall condition. For the boundary layer separation on blade suction surface and serious secondary flow near the end-wall, the effect of boundary layer suction （BLS） on the flow structure and performance of the supersonic compressor rotor have been investigated by two forms of suction： blade surface suction and the end-wall suction. The results show that： pressure ratio and efficiency of the compressor are all improved by the two forms of suction. By blade surface suction, the position of the shockwave can be changed, and the separation region is effectively reduced. The optimal position of blade suction is after the channel shockwave and where the boundary layer thickness has developed. Compared with the condition of no suction, the total pressure ratio increases 1.85% and efficiency increases 8.53% at the optimal suction flow rate. The inlet and exit flow angle has been improved by end-wall suction effectively and the optimal position of the end-wall suction is near the blade leading edge. The total pressure ratio increases 0.86% and efficiency increases 4.54% at the optimal suction flow rate with end-wall suction.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2011年第11期1843-1846,共4页
Journal of Engineering Thermophysics
基金
国家自然科学基金项目(No.50806061)
西北工业大学翱翔之星计划项目
关键词
跨音速压气机
附面层抽吸
抽吸位置
抽吸量
transonic compressor
boundary layer suction
suction position
suction flow rate
