摘要
以ROTOR37转子为例，采用数值模拟方法对叶尖压力面片削深度（沿叶片切向）及高度（沿叶片展高方向）进行参数化研究．计算得到60％，80％，90％及100％设计转速工况下的全工况特性曲线，并对100％设计转速工况作了详细的内部流场分析．包括原型在内10种模型计算结果表明：在0～50％片削深度和82％～100％展高内片削使ROTOR37转子堵塞流量、总压比、绝热效率略有提高，失速裕度略有下降，但影响并不十分显著．
Parameter studies for different attenuation thickness （in the tangential direction of blade） and relative height （in the spanwise direction of blade） of pressure surface at tip region are developed, which take ROTOR37 as an example and adopt numerical simulation to obtain the results. Aerodynamic performance curves are obtained at 60 %, 80 %, 90 % and 100% of design rotate speed working conditions, moreover, detailed analysis of internal flow field is presented for design condition. Results of ten models including the model with unchanged blade element indicate that blade tip attenuation within certain range can advance choke mass flow, total pressure ratio and adiabatic efficiency, and decrease stall margin of the rotor, however, the influence is not so patent.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第2期367-373,共7页
Journal of Aerospace Power
基金
国家自然科学基金资助项目(No.50376062)
关键词
航空
、航天推进系统
轴流压气机
叶尖片削
全工况
气动性能
数值模拟
aerospace propulsion system
axial-flow compressor
attenuated blade tip
overall working condition
aerodynamic performance
numerical simulation
