基于中弧线曲率控制的压气机叶型优化

doi:10.13675/j.cnki.tjjs.190344

推进技术 ›› 2020, Vol. 41 ›› Issue (8): 1740-1747.DOI: 10.13675/j.cnki.tjjs.190344

基于中弧线曲率控制的压气机叶型优化

孔庆国¹，杜旭博²，羌晓青³，张鸿¹

1.中国民航大学中欧航空工程师学院，天津 300300;2.西北工业大学动力与能源学院，陕西西安 710072;3.上海交通大学航空航天学院，上海 200240

发布日期:2021-08-15
基金资助:
江西省微小航空发动机重点实验室基金（Ef202080075）；中央高校基本科研业务费中国民航大学专项（3122019182）。

Compressor Airfoil Optimization Based on Camber Curvature Control

1.Sino-European Institute of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China;2.School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;3.School of Aeronautic and Astronautic,Shanghai Jiaotong University,Shanghai 200240,China

Published:2021-08-15

摘要/Abstract

摘要： 为提高压气机叶型优化设计水平，基于中弧线曲率控制方法编写了压气机叶片造型程序，将中弧线曲率控制参数作为优化变量，结合粒子群寻优算法对传统可控扩散叶型(CDA)进行了优化研究。结果表明：基于中弧线曲率控制的叶片造型程序能够对CDA叶型进行较好的拟合，拟合叶型的气动性能与设计要求较符。优化叶型在设计点的总压损失降低了约6.34%，优化叶型总压损失随攻角变化较为平缓。在一定攻角范围内，叶型中弧线曲率峰值的前移能够将吸力面马赫数峰值前移，提高叶型吸力面的扩压能力，降低总压损失。在大攻角工况下，改进的中弧线曲率分布能够显著降低叶型总压损失。将中弧线曲率控制参数作为优化变量进行CDA叶型的优化是可行的。

关键词: 造型程序;中弧线曲率;可控扩散叶型;叶型优化;压气机

Abstract: To improve the optimization quality of compressor blade, the compressor blade modeling program was developed based on the control-curvature-construction-method of the camber. The curvature control parameters of camber were taken as optimization variables. A traditional Controllable Diffusion Airfoil (CDA) was optimized by using the particle swarm optimization algorithm. Results show that the baseline CDA could be well fitted by using the blade modeling program, and the aerodynamic performance of the fitted airfoil is in conformity with the design requirements. The total pressure loss of the airfoil is reduced by 6.34% at the design point, while the total pressure loss curve of the optimized airfoil is flatter than the baseline. In a certain range of angle of attack, moving the peak curvature of the camber forward could move the peak of the Mach number on the suction surface forward and increase the diffusion capacity, which helps to reduce the total pressure loss of the airfoil. The total pressure loss was significantly reduced with the help of camber curvature distribution of the optimized airfoil under high angles of attack. It is feasible to optimize the design of CDA by using the camber curvature control parameter as the optimization variables.

Key words: Blade modeling program;Camber curvature;Controlled diffusion airfoil;Airfoil optimization;Compressor

孔庆国，杜旭博，羌晓青，张鸿. 基于中弧线曲率控制的压气机叶型优化[J]. 推进技术, 2020, 41(8): 1740-1747.

KONG Qing-guo¹, DU Xu-bo², QIANG Xiao-qing³, ZHANG Hong¹. Compressor Airfoil Optimization Based on Camber Curvature Control[J]. Journal of Propulsion Technology, 2020, 41(8): 1740-1747.

参考文献

[1] 周正贵. 压气机叶片自动优化设计[J]. 航空动力学报, 2002， 17(3): 305-308.
[2] Benini E， Toffolo A. Development of High-Performance Airfoils for Axial Flow Compressors Using Evolutionary Computation[J]. Journal of Propulsion and Power， 2002， 18(3): 544-554.
[3] Li J， Satofuka N. Optimization Design of a Compressor Cascade Airfoil Using a Navier-Stokes Solver and Genetic Algorithms[J]. Proceedings of the Institution of Mechanical Engineers， Part A： Journal of Power and Energy， 2002， 216(2): 195-202.
[4] Myoren C， Takahashi Y， Kato Y. A Multi-Objective Optimization of Three-Dimensional Blade Shape for an Axial Compressor Rotor in Transonic Stage[J]. Journal of the Gas Turbine Society of Japan， 2013， 40: 221-227.
[5] 张晓东，吴虎，黄健，等. 跨音速轴流压气机叶片造型及数值仿真[J]. 计算机仿真， 2008， 25(12): 58-61.
[6] Oyama A， Liou M S， Obayashi S. Transonic Axial-Flow Blade Optimization: Evolutionary Algorithms/Three-Dimensional Navier-Stokes Solver[J]. Journal of Propulsion and Power， 2004， 20(4): 612-619.
[7] Chen N， Zhang H， Xu Y， et al. Blade Parameterization and Aerodynamic Design Optimization for a 3D Transonic Compressor Rotor[J]. Journal of Thermal Science， 2007， 16(2): 105-114.
[8] Korakianitis T， Hamakhan I， Rezaienia A， et al. Two- and Three-Dimensional Prescribed Surface Curvature Distribution Blade Design (CIRCLE) Method for the Design of High Efficiency Turbines， Compressors， and Isolated Airfoils[J]. Journal of Turbomachinery， 2013， 135(4).
[9] Shen X， Avital E， Rezaienia A， et al. Computational Methods for Investigation of Surface Curvature Effects on Airfoil Boundary Layer Behavior[J]. Journal of Algorithms and Computational Technology， 2017， 11(1): 68-82.
[10] Sommer L， Bestle D. Curvature Driven Two-Dimensional Multi-Objective Optimization of Compressor Bade Sections[J]. Aerospace Science and Technology， 2011， 15(4): 334-342.
[11] Koller U， Monig R， Kusters B， et al. Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines，Part I: Design and Optimization[J]. Journal of Turbomachinery， 2000， 122(3): 397-405.
[12] Samad A， Kim K Y. Shape Optimization of an Axial Compressor Blade by Multi Objective Genetic Algorithm[J]. Proceedings of the Institution of Mechanical Engineers， Part A： Journal of Power and Energy， 2008， 222(6): 599-611.
[13] 金东海，展昭，桂幸民. 基于混合遗传算法的压气机叶型自动优化设计[J]. 推进技术， 2006， 27(4):349-353.
[14] 罗明，左志涛，李弘扬，等. 基于BP人工神经网络的离心压气机叶轮多目标优化设计方法[J]. 航空动力学报， 2016， 31(10): 2424-2431.
[15] 曲爱民. 模拟退火算法在三维气动优化设计中的应用[J]. 汽轮机技术， 2006， 48(3): 171-173.
[16] 宁方飞，刘晓嘉. 一种新的响应面模型及其在轴流压气机叶型气动优化中的应用[J]. 航空学报， 2007， 28(4): 813-820.
[17] Yang B， Xu Q， He L， et al. A Novel Global Optimization Algorithm and Its Application to Airfoil Optimization[J]. Journal of Turbomachinery， 2015， 137(4).
[18] 宋召运，刘波，程昊，等. 基于改进粒子群算法的串列叶型优化设计[J]. 推进技术， 2016， 37(8): 1469-1476.
[19] 施法中. 计算机辅助几何设计与非均匀有理B样条[M]. 北京:北京航空航天大学出版社， 1994.
[20] Jiang B， Zheng Q， Zhang H， et al. Advanced Axial Compressor Airfoils Design and Optimization[R]. ASME GT 2015-43846.
[21] Steinert W W， Eisenberg B B， Starken HH. Design and Testing of a Controlled Diffusion Airfoil Cascade for Industrial Axial Flow Compressor Application[J]. Journal of Turbomachinery， 1991， 113(4): 583-590.

基于中弧线曲率控制的压气机叶型优化

Compressor Airfoil Optimization Based on Camber Curvature Control

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