流体机械2016，Vol.44Issue(6)：24-28,16,6.DOI:10.3969/j.issn.1005-0329.2016.06.005
十级高压压气机气动方案设计的优化
Aerodynamic Preliminary Design Optimization of Ten-stage High Pressure Compressor
摘要
Abstract
The efficiency models Firstly,was improved based on the HARIKA program.The stalling pressure rise method pro-posed by C.C.Koch was used to predict stall margin of axial flow compressors.Then,the modified program was applied to cal-culate the characteristic of a ten-stage compressor.The results show that the accuracy of predicting stall margin achieves 99%. Finally,the NSGA-II was used to optimize the overall aerodynamic design.After optimization,the compressor peak efficiency at the design rotational speed increase by 3.4% compared to the initial characters and its surge margin increase from 1 1.6% to 17.6%.The off-design performances also increase by optimizing the angles of both the inlet guide vanes and the former five vanes.The character lines of 90% design rotational speed shows a higher peak efficiency and surge margin after optimization the stator value.关键词
高压压气机/气动方案设计/效率模型/可调静叶角度/优化Key words
high pressure compressor/aerodynamic preliminary design/efficiency model/variable stator value/optimization分类
机械制造引用本文复制引用
斯夏依,钟勇健,滕金芳,刘程远,羌晓青..十级高压压气机气动方案设计的优化[J].流体机械,2016,44(6):24-28,16,6.基金项目
国家自然科学基金项目（51576124）；2011先进航空发动机协同创新中心项目 （）
