摘要
为了提高高负荷轴流压气机气动性能,探索高负荷压气机设计方法。首先,对高负荷压气机轴向载荷和参数分布进行研究与筛选优化;然后,利用二维正/反问题设计与分析方法优化压气机载荷展向分布;最后,利用三维流场分析方法进行精细分析,从而使高负荷压气机级间参数达到良好的匹配。将该方法应用于一台高负荷压气机设计中,并将试验值与计算结果进行了比较分析。结果显示:该技术有效地提高了压气机全工况的性能,使压气机各级工作在合理的参数下,相对于第4代发动机的压气机平均级压比提高了16%,效率提高了1%。
In order to improve the aerodynamic performance of the high load axial-flow compressor and to explore the design method for the high load compressor.The axial load and parameter distribution of the high load compressor is studied and selectively optimized.The span load distribution of the compressor is then optimized using 2Ddirect and inverse solution design and analysis method.3Dflow filed analysis is applied to conduct refinement analysis.Stage parameters of the high load compressor are matched well.The method is used to design one high load compressor.Test results and calculation results are compared and studied.Results show that this technique can effectively improved compressor performance under all operation conditions and can allow the compressor to work with reasonable parameters at each stage.With this design technique,the average stage pressure ratio of the compressor can be increased by 16% and efficiency can be increased by 1%over the 4th generation aero-engine compressor.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2017年第9期156-166,共11页
Acta Aeronautica et Astronautica Sinica
关键词
高负荷
轴流压气机
级间匹配
优化
试验验证
high load
axial-flow compressor
stage matching
optimization
test verification
