流体机械

2016, v.44;No.528(06) 24-28+16

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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

斯夏依;钟勇健;滕金芳;刘程远;羌晓青;
SI Xia-yi;ZHONG Yong-jian;TENG Jin-fang;LIU Cheng-yuan;QIANG Xiao-qing;Shanghai Jiaotong University;AVIC Commercial Aircraft Engine Co.,Ltd.;

摘要(Abstract):

对HARIKA程序进行改进,创新性地修正了效率模型并引入Koch失速静压升系数模型,采用E3十级高压压气机气动特性试验数据验证此改进HARIKA程序,结果表明改进HARIKA程序对压气机100%转速失速边界的预估精度达到了99%。采用NSGA-II多目标遗传算法进行气动方案设计优化,优化后的方案与初始方案相比设计点的总效率提高了3.4%,喘振裕度提高了6%;通过调节进口导叶和前五级静子叶片的安装角,使得优化方案在非设计转速下的特性也得到了提高。
The efficiency models Firstly,was improved based on the HARIKA program. The stalling pressure rise method proposed by C. C. Koch was used to predict stall margin of axial flow compressors. Then,the modified program was applied to calculate 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 11. 6% to17. 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(KeyWords): 高压压气机;气动方案设计;效率模型;可调静叶角度;优化
high pressure compressor;aerodynamic preliminary design;efficiency model;variable stator value;optimization

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基金项目(Foundation): 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

作者(Author): 斯夏依;钟勇健;滕金芳;刘程远;羌晓青;
SI Xia-yi;ZHONG Yong-jian;TENG Jin-fang;LIU Cheng-yuan;QIANG Xiao-qing;Shanghai Jiaotong University;AVIC Commercial Aircraft Engine Co.,Ltd.;

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