基于系统辨识技术的叶轮机非定常气动力建模方法

doi:CNKI:11-1929/V.20110906.1124.005

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

基于系统辨识技术的叶轮机非定常气动力建模方法

苏丹¹, 张伟伟¹, 张陈安², 叶正寅¹

1. 西北工业大学翼型叶栅空气动力学国家重点实验室, 陕西西安 710072;
2. 中国科学院力学研究所, 北京 100190

收稿日期:2011-05-24 修回日期:2011-07-01 出版日期:2012-02-25 发布日期:2012-02-24
通讯作者: 张伟伟 E-mail:aeroelastic@nwpu.edu.cn
作者简介:苏丹男,硕士研究生.主要研究方向:叶轮机气动弹性力学. E-mail: sudan616@126.com
张伟伟男,博士,副教授.主要研究方向:流固耦合力学与控制. Tel: 029-88491342 E-mail: aeroelastic@nwpu.edu.cn
基金资助:
国家自然科学基金

An Unsteady Aerodynamic Modeling for Turbomachinery Based on System Identification

SU Dan¹, ZHANG Weiwei¹, ZHANG Chen'an², YE Zhengyin¹

1. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China;
2. Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

Received:2011-05-24 Revised:2011-07-01 Online:2012-02-25 Published:2012-02-24

摘要/Abstract

摘要： 为了快速获得不同刚度的叶轮机叶片颤振特性,提出了一种基于系统辨识技术的叶片排非定常气动力建模方法,分析了叶片气动阻尼随叶间相角差和固有频率的变化特性.该方法通过对多叶片通道的某一叶片单独施加一个扫频振动信号,求解一次非定常流场,得到叶片排上每个叶片的气动力响应,通过系统辨识,获得每个叶片的气动力频率响应.根据小扰动流的叠加原理,得到扫频范围内各固有频率下的叶片排所有叶片共同激励的气动力模型,由此进一步得到各个不同固有频率的所有叶间相角差下的气动阻尼.针对STCF4(Standard Test Configuration 4)算例,该方法的计算结果与直接采用计算流体力学(CFD)方法和直接采用谐振信号的降阶方法(ROM)得到的气动阻尼系数吻合得很好.该方法只需进行一次非定常CFD计算就能得到扫频范围内不同固有频率下的气动阻尼特性曲线,极大地提高了计算效率,方便了叶轮机设计初期的气动弹性稳定性参数分析.

关键词: 颤振, 计算流体力学, 降阶模型, 系统辨识, 叶轮机, 气动弹性

Abstract: This paper presents an efficient and fidelity-oriented unsteady aerodynamic modeling method that can investigate flutter for turbomachinery. A certain blade of multiple blade passages is specified vibrating at a swept-frequency signal instead of harmonic one, and forced aerodynamic responses of the blade row can first be calculated. Identify form the aerodynamic responses data, so that the frequency responses of the system for muti-passages are acquired, and the aerodynamic coefficient of every blade for different natural frequencies within swept-frequencies can be obtained immediately. Following the superposition principle of small disturbance flow, aerodynamic damping coefficients changing with inter blade phase angles as well as frequencies are acquired only by an unsteady computational fluid dynamics(CFD)computation. The aeroelastic characteristics of STCF4 (Standard Test Configuration 4) are analyzed by using this method. The results for different na- tural frequencies are agreed well with that of reduced order model(ROM)method as well as direct CFD method, and the computational efficiency is improved obviously, as a result, this method is useful to analyze stability during preliminary design of turbomachinery.

Key words: flutter, computational fluid dynamics, reduced order model, system identification, turbomachinery, aeroelasticity

中图分类号:

V211.47

苏丹, 张伟伟, 张陈安, 叶正寅. 基于系统辨识技术的叶轮机非定常气动力建模方法[J]. 航空学报, 2012, 33(2): 242-248.

SU Dan, ZHANG Weiwei, ZHANG Chen'an, YE Zhengyin. An Unsteady Aerodynamic Modeling for Turbomachinery Based on System Identification[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(2): 242-248.

参考文献

[1] Zhou S. Introduction of turbomachinery aeroelasticity. Bejing: National Defense Industry Press, 1989: 7-35. (in Chinese) 周盛. 叶轮机气动弹性力学引论. 北京: 国防工业出版社, 1989: 7-35.

[2] Yang X D, Tang Z M, Zhou S. A semiactuator disk method for predicting the blade stall flutter. Journal of Beijing Insititute of Aeronautic and Astronautic, 1986(4): 93-101. (in Chinese) 杨晓东, 唐智明, 周盛. 预测叶片失速颤振的一种半激盘方法. 北京航空学院学报, 1986(4): 93-101.

[3] Yang X D, Tao D P, Zhou S. Discussion of a basic assumptions for turbomachinery aeroelasticity. Science in China: Series A, 1991(2): 192-199. (in Chinese) 杨晓东, 陶德平, 周盛. 对于叶轮机气动弹性力学一个基本假设的讨论. 中国科学: A辑, 1991(2): 192-199.

[4] Lane F. System mode shapes in the flutter of compressor blade rows. Journal of the Aeronautical Sciences, 1956(23): 54-66.

[5] BakhleM A, Reddy T S R, Keith T G K. Time domain flutter analysis of cascades using a full potential solver. AIAA Journal, 1992, 30(1): 163-170.

[6] Yang Q Z, Xiao J, Zhou X H. Cascade flutter investigation based on flow structure coupling unsteady flow. Journal of Propulsion Technology, 2005, 26(6): 526-530. (in Chinese) 杨青真, 肖军, 周新海. 基于气/固耦合非定常流动的叶栅颤振分析. 推进技术, 2005, 26(6):526-530.

[7] Sadeghi M, Yang S, Liu F. Computation of uncoupled and coupled aeroelasticity of three-dimensional blade rows. AIAA-2004-0192, 2004.

[8] Sadeghi M, Liu F. Investigation of non-linear flutter by a coupled aerodynamics and structural dynamics method. AIAA-2001-0573, 2001.

[9] Zhang W W, Ye Z Y. Effect of leading-edge vortex on flutter characteristics of high sweep angle wing. Acta Aeronautica et Astronautica Sinica, 2009, 30(12): 2263-2268. (in Chinese) 张伟伟, 叶正寅. 大后掠翼前缘涡对其颤振特性的影响研究. 航空学报, 2009, 30(12): 2263-2268.

[10] Zhang W W, Ye Z Y, Yang Q, et al. Gust response ana- lysis using CFD-based reduced order models. Chinese Journal of Theoretical and Applied Mechanics, 2008, 40(5): 593-598. (in Chinese) 张伟伟, 叶正寅, 杨青, 等. 基于ROM技术的阵风响应分析方法. 力学学报, 2008, 40(5): 593-598.

[11] Zhang W W, Ye Z Y, Zhang C A. ROM based aeroservoelastic analysis in transonic flow. Journal of Aircraft, 2009, 46(6): 2178-2183.

[12] Zhang W W, Ye Z Y. Control law design for transonic aeroservoelasticity. Aerospace Science and Technology, 2007, 11(2-3): 136-145.

[13] Zhang C A, Zhang W W, Ye Z Y, et al. An efficient method on aerodynamic damping coefficient calculation for turbomachinery. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(5): 826-833. (in Chinese) 张陈安, 张伟伟, 叶正寅, 等. 一种高效的叶轮机叶片气动阻尼计算方法. 力学学报, 2011, 43(5): 826-833.

[14] Mehra R K, Prasanth R K. Time-domain system identification methods for aeromechanical and aircraft structural modeling. Journal of Aircraft, 2004, 41(4): 721-729.

[15] Love R, Lind R. Identification of aeroservoelastic models from experimental flapping-wing deflections. AIAA-2009-5841, 2009.

[16] Salhi B, Lardies J, Berthillier M. Identification of modal parameters and aeroelastic coefficients in bladed disk assemblies. Mechanical Systems and Signal Processing, 2009(23): 1984-1908.

[17] Zhang W W, Ye Z Y. Numerical simulation of aeroelasti- city basing on identification technology of unsteady aerodynamic loads. Acta Aeronautica et Astronautica Sinica, 2006, 27(4): 579-583. (in Chinese) 张伟伟, 叶正寅. 基于非定常气动力辨识技术的气动弹性数值模拟. 航空学报, 2006, 27(4): 579-583.

[18] Stephens C H, Arena S A J, Gupta K K. CFD-based aeroservoelastic predictions with comparisons to benchmark experimental data. AIAA-1999-0766, 1999.

[19] Fang C Z, Xiao D Y. Process identification. Beijing: Tsinghua University Press, 2003: 71-80. (in Chinese) 方崇智, 萧德云. 过程辨识. 北京:清华大学出版社, 2003: 71-80.

[20] Blcs A, Fransson T H. Aeroelasticity in turbomachines-comparison of theoretical and experimental cascade results. ADA180534, 1986.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于系统辨识技术的叶轮机非定常气动力建模方法

An Unsteady Aerodynamic Modeling for Turbomachinery Based on System Identification

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	刘琦, 史勇杰, 胡志远, 徐国华. 共轴刚性旋翼气动及噪声特性的参数影响分析[J]. 航空学报, 2024, 45(9): 528856-528856.
[2]	张东飞, 高军辉. GPU加速高阶谱差分方法在风扇噪声中的应用[J]. 航空学报, 2024, 45(8): 128941-128941.
[3]	李国强, 宋奎辉, 覃晨, 赵光银, 吴霖鑫, 杨永东. 基于后缘小翼的翼型动态失速主动控制试验[J]. 航空学报, 2024, 45(3): 128699-128699.
[4]	张桂玮, 刘召庆, 朱镭, 张衡, 田玮, 李伟光, 杨智春. 地面颤振模拟试验技术研究进展[J]. 航空学报, 2024, 45(10): 29229-029229.
[5]	陆凤霞, 韦坤, 王春雷, 鲍和云, 朱如鹏. 直升机中减三相流金属屑末可达性[J]. 航空学报, 2024, 45(1): 128524-128524.
[6]	张程, 任浩源, 史泰龙, 戴雯迪. 含非线性连接的折叠舵全时域多学科耦合分析方法及应用[J]. 航空学报, 2023, 44(S2): 729461-729461.
[7]	喻世杰, 周兴华, 黄锐. 变弯度机翼参数化气动弹性建模与颤振特性分析[J]. 航空学报, 2023, 44(8): 227346-227346.
[8]	任炯, 王刚, 胡国栋, 石晓露. 自适应Walsh函数有限体积方法[J]. 航空学报, 2023, 44(8): 127444-127444.
[9]	陈浩宇, 王彬文, 宋巧治, 李晓东. 热颤振地面模拟试验技术[J]. 航空学报, 2023, 44(8): 227295-227295.
[10]	曹文博, 刘溢浪, 张伟伟. 基于降阶模型和梯度优化的流场加速收敛方法[J]. 航空学报, 2023, 44(6): 127090-127090.
[11]	王培涵, 吴志刚, 杨超, 孙晓旭. 一种适用于弹性飞机飞行仿真的补丁方法[J]. 航空学报, 2023, 44(6): 127038-127038.
[12]	刘为佳, 李映坤, 陈雄, 李春雷. 基于流固耦合的激波/边界层干扰作用下壁板颤振特性[J]. 航空学报, 2023, 44(6): 127085-127085.
[13]	王梓伊, 张伟伟, 刘磊, 杨肖峰. 适用于复杂流动的热气动弹性降阶建模方法[J]. 航空学报, 2023, 44(4): 126807-126807.
[14]	樊宇翔, 赵瑞, 左政玄, 杨光, 李宇. 气体引射效应对壁面热流和摩擦阻力的影响[J]. 航空学报, 2023, 44(21): 528587-528587.
[15]	刘思华, 王占莹, 李利剑, 张敏弟. 头型对射弹高速入水稳定性的影响[J]. 航空学报, 2023, 44(21): 528437-528437.