大连海事大学学报 >
2018 , Vol. 44 >Issue 1: 99 - 106
DOI: https://doi.org/10.16411/j.cnki.issn1006-7736.2018.01.015
基于弯掠参数控制的压气机动叶优化设计
收稿日期: 2017-08-02
修回日期: 2017-09-19
网络出版日期: 2017-09-19
基金资助
国家自然科学基金资助项目(51309063；51679051)；中央高校基本科研业务费专项资金资助项目(HEUCFP201720)．
Optimization design of compressor rotor based on bending-swept parameter control
Received date: 2017-08-02
Revised date: 2017-09-19
Online published: 2017-09-19
王忠义 , 曲锋 , 万雷 , 王萌 . 基于弯掠参数控制的压气机动叶优化设计[J]. 大连海事大学学报, 2018 , 44(1) : 99 -106 . DOI: 10.16411/j.cnki.issn1006-7736.2018.01.015
The performance of NASA Stage35 single stage axial compressor prototype was calculated by numerical simulation. The parameterized fitting of the rotor in the compressor was performed by selecting the reasonable number of the control points of Bezier and B-spline curve to produce a suitable parameterized geometric. Through controlling bending-swept characteristics parameter, the optimization design of compressor rotor was carried out by using artificial neural network and genetic algorithm for the purpose of adiabatic efficiency improvement. Compared with the reference blade, the aerodynamic performances of the optimized blade are improved obviously. The shock position can be changed by optimizing the bending-swept characteristics of the moving blade. The area of boundary layer and loss can be decreased, the structure of flow can be optimized, and the adiabatic efficiency of the compressor can be improved effectively.
[1]汪光文，周正贵，胡骏．基于优化算法的压气机叶片气动设计[J]．航空动力学报，2008，23(7)：1218 – 1224．
WANG Guang-wen，ZHOU Zheng-gui，HU Jun．Aerodynamic design of compressor blade using optimization algorithm[J]．Journal of Aerospace Power，2008，23(7)：1218 – 1224．(in Chinese)
[2]汪光文．基于并行遗传算法的风扇/压气机叶片气动优化设计[D]．南京：南京航空航天大学，2009．
WANG Guang-wen．Research on aerodynamic optimization design of fan/compressor blade using parallel genetic algorithm[D]．Nanjing：Nanjing University of Aeronautics and Astronautics，2009．(in Chinese)
[3]高坤．轴流压气机叶片优化设计及分析[D]．西安：西北工业大学，2007．
GAO Kun．Optimization and analysis of axial compressor blade[D]．Xi’an：Northwestern Polytechnical University，2007．(in Chinese)
[4]王娥．考虑转捩影响的地面重型燃气轮机压气机叶型优化设计[D]．哈尔滨：哈尔滨工业大学，2009．
WANG E．Blade optimization design for a ground-based heavy-duty gas turbine incorporating transition modeling[D]．Harbin：Harbin Institute of Technology，2009．(in Chinese)
[5]吴世勋．双级离心压气机气动分析与优化设计[D]．北京：中国科学院大学，2012．
WU Shi-xun．Aerodynamic analysis and optimum design of two-stage centrifugal compressor[D]．Beijing：University of Chinese Academy of Sciences，2012．(in Chinese)
[6]高修磊．多级轴流压气机气动分析及二维优化设计[D]．南京：南京航空航天大学，2012．
GAO Xiu-lei．Aerodynamic analysis and 2-D optimal design of multi-stage axial compressor[D]．Nanjing：Nanjing University of Aeronautics and Astronautics，2012．(in Chinese)
[7]JI Lu-cheng，LI Wei-wei，TIAN Yong，et al．Multi-stage turbomachinery blades optimization design using adjoint method and thin shear-layer N-S equations[C]//ASME Turbo Expo 2012：Turbine Technical Conference and Exposition．ASME，2012．
[8]罗钜．高性能风扇/压气机三维叶片气动设计与实验研究[D]．南京：南京航空航天大学，2013．
LUO Ju．Aerodynamic design of three-dimensional blades and experimental investigation for advanced fan/compressor[D]．Nanjing：Nanjing University of Aeronautics and Astronautics，2013．(in Chinese)
[9]苏赫．多级轴流式压气机内部流场分析和优化设计[D]．北京：中国科学院研究生院(工程热物理研究所)，2014．
SU He．Multi-stage axial compressor internal flow field analysis and design optimization[D]．The University of Chinese Academy of Sciences(Institute of Engineering Thermophysics)，2014．(in Chinese)
[10]ZIEGLER K，EISENBERG B，HÖRMEYER K，et al．Development of a novel axial compressor generation for industrial applications:part1—compressor design and performance[C]//ASME Turbo Expo 2014:Turbine Technical Conference and Exposition．ASME，2014．
[11]SONG Peng，SUN Jin-ju，WANG Ke．Blade shape optimization of transonic axial flow fan in terms of sectional profiles and stacking line[C]//ASME Turbo Expo 2014:Turbine Technical Conference and Exposition．ASME，2014．
[12]任平，朱芳，赵连会．跨音轴流压气机气动设计与数值优化[J]．动力工程学报，2015，35(5)：373 – 379．
REN Ping，ZHU Fang，ZHAO Lian-hui．Aerodynamic design and numerical optimization of a transonic axial flow compressor[J]．Journal of Chinese Society of Power Engineering，2015，35(5)：373 – 379．(in Chinese)
[13]JIANG Bin，ZHENG Qun，ZHANG Hai，et al．Advanced axial compressor airfoils design and optimization[C]//ASME Turbo Expo 2015:Turbine Technical Conference and Exposition．ASME，2015．
[14]JAMESON A，SCHMIDT W，TURKEL E．Numerical solution of the Euler equations by finite volume methods using Runge Kutta time stepping schemes[C]//14th Fluid and Plasma Dynamics Conference．AIAA，1981．
[15]MOORE R D，REID L．Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively,and with design pressure ratio of 2.05[R]．USA：NASA，1980．
[16]Charles Hirsch．User manual:FINETM/Design3D V2 optimization kernel[M]．NUMECA International，2006：
18 – 21．
[17]郭然，贾力平，樊小莉，等．NUMECA系列教程[M]．北京：机械工业出版社，2013：197 – 208．
/
| 〈 |
|
〉 |