吸附式压气机叶型及抽吸方案耦合优化设计

推进技术 ›› 2014, Vol. 35 ›› Issue (9): 1194-1201.

吸附式压气机叶型及抽吸方案耦合优化设计

刘　波,李　俊,杨小东,史　磊

西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072

发布日期:2021-08-15
作者简介:刘　波(1960—)，男，博士，教授，研究领域为叶轮机气动热力学。
基金资助:
国家自然科学基金重点资助项目(51236006)。

Coupling Optimization Design for Aspirated Compressor Airfoil and Aspirated Scheme

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

Published:2021-08-15

摘要/Abstract

摘要： 为了探索吸附式叶型设计特点，研究了一种将叶型和抽吸方案耦合优化的新型吸附式压气机叶型设计方法。该方法利用人工蜂群算法结合准三维叶栅通道计算程序对吸附式叶型进行耦合优化设计。在进口马赫数为0.7，攻角1.9°的设计工况下，将耦合优化得到的优化设计方案与先优化叶型再优化抽吸方案得到的原始设计方案进行了对比分析，并且对耦合优化前后的设计方案均进行了风洞吹风实验，验证了耦合优化设计方法的准确性和实际应用性。研究结果表明:耦合优化设计之后总压损失降低了27%，负荷提高了2%。适当改变叶型前缘半径，可以推迟附面层转捩位置，减小气流的摩擦损失，使附面层流动更为合理。针对本文的设计工况，更均匀的弯度变化会提高吸附式叶型的设计效果。本文在54%相对弦长处并配合0.75%的抽吸量，可以有效地控制叶型分离，降低抽吸所需要的能量。

关键词: 吸附式压气机；耦合优化设计；叶栅吹风实验

Abstract: In order to explore the design characteristics of the aspirated airfoil，a new optimization design method coupling airfoil and aspirated scheme was presented. This method was developed for coupling optimization，which combined Artificial Bee Colony Algorithm(ABC)and quasi-three dimensional cascade calculation programme. The design condition is that inlet Mach number is 0.7 and incidence is 1.9°.In the design condition，comparison and analysis were made between coupling optimized design scheme and original design scheme. And cascade wind tunnel experiment was conducted to demonstrate the optimization effect. Research results show that the coupling optimized design can make the total pressure loss reduce by 27% ，and the load increase by 2%. Appropriate changing blade leading edge radius can delay the boundary layer transition position，reduce the flow friction loss，and make the boundary layer flow more reasonable. In this paper design condition，more uniform load distribution can improve the aspirated airfoil design performance. Aspirated scheme that has suction location in 54% relative chord combined with suction air flow rate of 0.75%，can effectively control boundary layer separation，and reduce the energy output on suction.

Key words: Aspirated compressor；Coupling optimized design；Cascade wind tunnel experiment

刘　波,李　俊,杨小东,史　磊. 吸附式压气机叶型及抽吸方案耦合优化设计[J]. 推进技术, 2014, 35(9): 1194-1201.

LIU Bo ,LI Jun,YANG Xiao-dong,SHI Lei. Coupling Optimization Design for Aspirated Compressor Airfoil and Aspirated Scheme[J]. Journal of Propulsion Technology, 2014, 35(9): 1194-1201.

参考文献

[1] Gmelin C,Thiele F,Liesner K,et al.Investigations of Secondary Flow Suction in a High Speed Compressor Cascade[R].ASME 2011-GT-46479.
[2] Liesner K,Meyer R,Lemke M,et al.On the Efficiency of Secondary Flow Suction in a Compressor Cascade[R].ASME 2010-GT-22336.
[3] Lord W K,MacMartin D G,Tillman T G.Flow Control Opportunities in Gas Turbine Engines[R].AIAA 2000-2234.
[4] Merchant A A.Design and Analysis of Axial Aspirated Compressor Stage[D].Boston:Massachusetts Institute of Technology,1999.
[5] Schuler B J.Experimental Investigation of an Aspirated Fan Stage[D].Boston:Massachusetts Institute of Technology,2001.
[6] Merchant A A.Aerodynamic Design and Performance of Aspirated Airfoils[J].Journal of Turbomachinery,2003,125(1):141-148.
[7] Godard A,Fourmaux A,Burguburu S,et al.Design Method of a Subsonic Aspirated Cascade[R].ASME 2008-GT-50835.
[8] Godard A,Fourmaux A,Burguburu S,et al.Experimental and Numerical Study of a Subsonic Aspirated Cascades[R].ASME 2012-GT-69011.
[9] Schuler B J,Kerrebrock J L,Merchant A A.Experimental Investigation of a Transonic Aspirated Compressor[J].Journal of Turbomachinery,2005,127(4):340-348.
[10] Merchant A A,Kerrebrock J L,Adamczyk J J,et al.Experimental Investigation of a High Pressure Ratio Aspirated Fan Stage[J].Journal of Turbomachinery,2005,127(1):43-51.
[11] Mark Drela.Two-Dimensional Transonic Aerodynamic Design and Analysis Using the Euler Equations[D].Boston:Massachusetts Institute of Technology,1985.
[12] Markus Olhofer ,Yaochu Jin.Adaptive Encoding for Aerodynamic Shape Optimization Using Evolution Strategies[R].IEEE,2001.
[13] 薛亮,韩万金.基于遗传算法与近似模型的全局气动优化方法[J].推进技术,2008,29(3): 360~366.(XUE Liang,HAN Wan-jin.Global Aerodynamic Optimization Method Using Genetic Algorithms and Surrogate Model[J].Journal of Propulsion Technology,2008,29(3): 360~366.)
[14] 周正贵.高亚声速压气机叶片优化设计[J].推进技术,2004,25(1): 58～61.(ZHOU Zheng-gui.Optimization of High Subsonic Axial Compressor Blades[J].Journal of Propulsion Technology,2004,25(1):58~61.)
[15] Guo Peng,Cheng Wenming and Liang Jian.Global Artificial Bee Colony Search Algorithm for Numerical Function Optimization[R].IEEE,2011.
[16] 段海滨,张祥银,徐春芳.仿生智能计算[M].北京:科学出版社,2011: 88-104.
[17] 航空发动机设计手册总编委会.发动机设计手册第8册压气机[M].北京: 航空工业出版社,2000:126-127.(编辑:史亚红)收稿日期:2013-07-16；修订日期:2014-02-27。基金项目:国家自然科学基金重点资助项目(51236006)。作者简介:刘波(1960—),男,博士,教授,研究领域为叶轮机气动热力学。E-mail:liujun7manunited@163.com