压气机S形转接段半反问题设计方法研究

单鹏; 吕振涛

压气机S形转接段半反问题设计方法研究

单鹏,
吕振涛

北京航空航天大学能源与动力工程学院, 北京 100191

计量
- 文章访问数: 1244
- HTML浏览量: 5
- PDF量: 897
- 被引次数: 0
出版历程
- 收稿日期: 2012-10-16
- 刊出日期: 2013-10-28

Half-inverse problem for design of S-shaped compressor transition duct

School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 研究了压气机部件间S形转接段的气动设计方法,提出了一种控制转接段壁面静压梯度等参数的半反问题设计,并发展了相应设计程序.采用所述方法,对某轴流-离心压气机转接段进行了设计验证.结果表明:通过调整反问题设计参数,可以自由控制内壁面的静压分布及壁面几何,又通过对外壁面几何进行数值匹配,能够很好地实现所设计的内壁面上的静压分布,验证了本方法可行.在未寻求最优内壁面静压梯度分布的情况下,进口高度长度比达0.138,轮毂半径差长度比达0.485的轴对称转接段的总压恢复系数可达0.98以上.
- 压气机 /
- S形转接段 /
- 反问题 /
- 静压梯度 /
- 遗传算法
Abstract: An aerodynamic design method of S-shaped transition duct between compressor components was studied. Based on the control of wall static pressure gradient of the transition duct, etc, a half-inverse problem design strategy was proposed, and the corresponding design code was developed. To verify the feasibility of the method, a transition duct for axial-centrifugal compressor was designed by the method mentioned above. The result shows that the static pressure distribution on inner wall along with its geometry can be controlled freely by adjusting the inverse design parameters. The designed static pressure distribution on inner wall can be realized through the numerical matching procedure of the outer wall geometry. The design method is practicable since the total pressure recovery coefficient of the axial-symmetric transition duct can be above 0.98 without searching the optimal static pressure gradient distribution on inner wall, when the duct parameters of inlet-height/length ratio is 0.138, and hub-radius-difference/length ratio is 0.485.
- compressor /
- S-shaped transition duct /
- inverse problem /
- static pressure gradient /
- genetic algorithm

HTML

参考文献(15)

[1]	Dominy R G,Kirkham D A,Smith A D.Flow development through inter-turbine diffusers[R].ASME Paper 96-GT-139,1996.
[2]	Norris G,Dominy R G,Smith A D.Strut influences within a diffusing annular S-shaped duct[R].ASME Paper 98-GT-425,1998.
[3]	Ortiz D C,Miller R J,Hodson H P.Effect of length on compressor inter-stage duct performance[R].ASME Paper GT2007-27378,2007.
[4]	Sonodo T,Arima T,Oana M.The influence of downstream passage on the flow within an annular S-shaped duct[J].Journal of Turbomachinery,1998,120(4):714-722.
[5]	Bailey D W,Britchford K M,Carrotte J F,et al.Performance assessment of an annular S-shaped duct[J].Journal of Turbomachinery,1997,119(1):149-156.
[6]	Wallin F,Eriksson L E.Response surface-based transition duct shape optimization[R].ASME Paper GT2006-90978,2006.
[7]	Ghisu T,Molinari M,Parks G,et al.Axial compressor intermediate duct design and optimization [R].AIAA-2007-1868,2007.
[8]	阙晓斌,侯安平,周盛.基于壁面压力梯度控制的压气机S形过渡段设计[J].航空学报,2010,31(3):459-465. QUE Xiaobin,HOU Anping,ZHOU Sheng.S-shaped compressor transition duct design based on wall pressure gradient control[J].Acta Aeronautica et Astronautica Sinica,2010,31(3):459-465.(in Chinese)
[9]	Holland J H.Adaptation in natural and artificial system:an introductory analysis with applications to biology,control,and artificial intelligence[M].Massachusetts,US:Massachusetts Institute of Technology Press,1992.
[10]	Goldberg D E.Genetic algorithms in search,optimization,and machine learning[M].Massachusetts,US:Addison-Wesley Publishing Company,1989.
[11]	周明,孙树栋.遗传算法原理及应用[M].北京:国防工业出版社,1999.
[12]	王丽薇.遗传算法的研究与应用[D].哈尔滨:哈尔滨工业大学,1994. WANG Liwei.The research and application of genetic algorithm [D].Harbin:Harbin Institute of Technology,1994. (in Chinese)
[13]	王晓鹏.遗传算法及其在气动优化设计中的应用研究[D].西安:西北工业大学,2000. WANG Xiaopeng.Genetic algorithm and its application research in aerodynamic optimization design [D].Xi'an:Northwestern Polytechnical University,2000.(in Chinese)
[14]	脱伟,熊劲松,侯安平,等.遗传算法在多级压气机气动优化设计中的应用[J].航空动力学报,2007,22(2):305-309. TUO Wei,XIONG Jinsong,HOU Anping,et al.Application of genetic algorithm to multi-stage compressor aerodynamic optimization design[J].Journal of Aerospace Power,2007,22(2):305-309.(in Chinese)
[15]	何柳.基于气动变量参数化的轴流压气机三维气动数值优化[D].北京:北京航空航天大学.2010. HE Liu.Three-dimensional aerodynamic optimization for axial-flow compressors based upon the aerodynamic parameters [D].Beijing:Beijing University of Aeronautics and Astronautics,2010.(in Chinese)