商用发动机10级高压压气机一维特性优化设计

史磊; 刘波; 张鹏; 李俊; 王雷

商用发动机10级高压压气机一维特性优化设计

西北工业大学动力与能源学院, 西安 710072

基金项目: 国家自然科学基金(50976093)

计量
- 文章访问数: 1677
- HTML浏览量: 3
- PDF量: 1235
- 被引次数: 0
出版历程
- 收稿日期: 2012-07-10
- 刊出日期: 2013-07-28

One-dimensional characteristic optimization design for ten-stage high pressure compressor in commercial engine

School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 采用HARIKA算法对某商用发动机10级高压压气机进行了一维特性预测.引入遗传算法优化设计手段,以压气机一维设计参数为优化变量,设计转速下特性线的峰值效率、裕度为优化目标函数.与初始特性线相比,压气机在优化后设计转速时特性线的峰值效率提高了12.3%,裕度由11.7%提高到25.13%.对变几何压气机特性进行了优化分析,给出不同换算转速下进口导叶及前3级静子叶片安装角的最佳调节规律.优化后的压气机在非设计转速下的效率特性得到了大幅提升,压比特性得到了提高,流通能力也得到了加强.将压气机一维优化的特性线与采用一维优化设计参数得到的全三维计算结果在1.0,0.9倍换算转速下进行了对比,两者预测出的喘振边界在最大偏差处不超过6.25%.
- HARIKA算法 /
- 特性计算 /
- 遗传算法 /
- 变几何压气机 /
- 一维优化设计
Abstract: HARIKA algorithm was applied to simulate the characteristic of a ten-stage high pressure compressor. With introduction of genetic algorithm (GA), one-dimensional design parameters were selected as optimum variables, and functions containing peak efficiency and margin were used as optimization objectives. Compared with initial characteristic, peak efficiency of characteristic after optimization at designed speed increased by 12.3%, and its margin increased from 11.7% to 25.13%. Then HARIKA algorithm was used to simulate variable geometry compressor characteristics. Setting angles of inlet guide vane and first three stage stators after optimization at different engine corrected speeds were presented. The performance characteristics of compressor including peak efficiency, peak pressure and flow margin were improved to great extent. Calculation results of compressor characteristics in one-dimensional and three-dimensional were compared at engine corrected speed of 1.0, 0.9. The maximum deviation of their margin was not more than 6.25%.
- HARIKA algorithm /
- characteristic calculation /
- genetic algorithm /
- variable geometry compressor /
- one-dimensional optimization design

HTML

参考文献(15)

[1]	Johnson M.One-dimensional,stage-by-stage,axial compressor performance model [R].ASME Paper 1991-GT-192,1991.
[2]	舒士甄,朱力,柯玄龄,等.叶轮机械原理[M].北京:清华大学出版社,1991.
[3]	胡骏.均匀与非均匀进气条件下多级轴流压气机性能计算:均匀进气及径向畸变的影响[J].航空动力学报,2000,15(3):225-228. HU Jun.Calculation of off-design performance of multistage compressors with uniform and radial distorted inlet flow[J].Journal of Aerospace Power,2000,15(3):225-228.(in Chinese)
[4]	李立君,黄杰,唐狄毅,等.轴流压气机特性预测[J].西北工业大学学报,2003,21(1):71-73. LI Lijun,HUANG Jie,TANG Diyi,et al.An accurate method for predicting performance characterictics of multi-stage axial compressor[J].Journal of Northwestern Polythchnical University,2003,21(1):71-73.(in Chinese)
[5]	陈江,刘太秋,李孝堂,等.五级轴流压气机气动设计数值研究[J].工程热物理学报,2010,31(6):943-946. CHEN Jiang,LIU Taiqiu,LI Xiaotang,et al.Aerodynamic design of five stage axial compressor by numerical simulation[J].Journal of Engineering Thermophysics,2010,31(6):943-946.(in Chinese)
[6]	李志刚,陶增元,丁康乐,等.一种改进的变几何压气机特性计算方法[J].航空发动机,2004,30(4):7-9. LI Zhigang,TAO Zengyuan,DING Kangle,et al.Simulation of variable geometry compressor characterictics[J].Aeroengine,2004,30(4):7-9.(in Chinese)
[7]	唐狄毅,宋文艳.压气机总特性与级特性相关性研究 [D].西安:西北工业大学,2001. TANG Diyi,SONG Wenyan.Research in the relation between total compressor characteristic and single-stage characteristic [D].Xi'an:Northwestern Polytechnical University,2001.(in Chinese)
[8]	张琛,詹志辉.遗传算法选择策略比较[J].计算机工程与设计,2009,30(23):5471-5478. ZHANG Chen,ZHAN Zhihui.Comparison of selection strategy in genetic algorithm[J].Computer Engineering and Design,2009,30(23):5471-5478.(in Chinese)
[9]	Day I J,Freeman C.The unstable behavior of low and high-speed compressors[R].ASME Paper 1993-GT-26,1993.
[10]	Gresh M T.Compressor performance:selection,operation,and testing of axial and centrifugal compressor[M].Oxford:Butterworth-Heinemann,1991.
[11]	张健,任铭林.静叶角度调节对压气机性能影响的试验研究[J].航空动力学报,2000,15(1):27-30. ZHANG Jian,REN Minglin.Experimental investigation on effect of stator vane angle adjustment on compressor performance[J].Journal of Aerospace Power,2000,15(1):27-30.(in Chinese)
[12]	Steinke R J.Design of 9.271 pressure-ratio five-stage core compressor and overall performance for first three stages.NASA TP-3597,1986.
[13]	Sun J,Elder R L.Numerical optimization of a stator vane setting in multistage axial-flow compressors[J].Journal of Power and Energy:Part A,1998,212(4):247-259.
[14]	刘波,周新海,严汝群.轴流压气机可控扩散叶型的数值优化设计[J].航空动力学报,1991,6(1):9-12. LIU Bo,ZHOU Xinhai,YAN Ruqun.Numerical optimization program for designing controlled diffusion compressor blading[J].Journal of Aerospace Power,1991,6(1):9-12.(in Chinese)
[15]	姜斌,吴晓鹏,王松涛.压气机分层优化气动设计体系研究[J].热能动力工程,2009,24(6):719-724. JIANG Bin,WU Xiaopeng,WANG Songtao.A study of an aerodynamic design system for the layered optimization of a compressor[J].Journal of Engineering for Thermal Energy and Power,2009,24(6):719-724.(in Chinese)