航空学报 > 2014, Vol. 35 Issue (12): 3232-3243   doi: 10.7527/S1000-6893.2014.077

基于CFD技术的高效叶栅耦合颤振分析方法

苏丹1, 张伟伟1, 全金楼1, 马明生2, 叶正寅1   

  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. 中国空气动力研究与发展中心 计算空气动力研究所, 四川 绵阳 621000
  • 收稿日期:2014-01-08 修回日期:2014-04-24 出版日期:2014-12-25 发布日期:2014-06-03
  • 通讯作者: 张伟伟 男, 博士, 教授, 博士生导师.主要研究方向: 流固耦合力学与流动控制. Tel: 029-88481342 E-mail: aeroelastic@nwpu.edu.cn E-mail:aeroelastic@nwpu.edu.cn
  • 作者简介:苏丹 男, 博士研究生.主要研究方向: 叶轮机气动弹性分析. Tel: 029-88481342 E-mail: sudan616@126.com
  • 基金资助:

    国家自然科学基金(11172237)

An Efficient Coupled Method of Cascade Flutter Analysis by Using CFD Technique

SU Dan1, ZHANG Weiwei1, QUAN Jinlou1, MA Mingsheng2, YE Zhengyin1   

  1. 1. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China;
    2. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2014-01-08 Revised:2014-04-24 Online:2014-12-25 Published:2014-06-03
  • Supported by:

    National Natural Science Foundation of China (11172237)

摘要:

为了考虑叶轮机叶片结构与流体之间的耦合效应,同时提高叶轮机颤振数值研究的效率,发展了一种基于非定常气动力降阶模型(ROM)的叶栅耦合颤振分析方法.该方法运用时域计算流体力学(CFD)技术计算少数几个叶片的非定常气动力,通过系统辨识及一些假设构建整个叶栅振动的非定常气动力降阶模型,并在状态空间耦合叶栅结构动力学方程建立叶栅气动弹性方程,采用特征值和时域仿真分析该系统稳定性.运用该降阶耦合方法对STCF4(Standard Test Configuration 4)以及NASA Rotor67叶栅系统的稳定性进行了计算.通过与直接计算流体力学/计算结构动力学(CFD/CSD)耦合方法和非耦合方法计算结果的比较验证了该方法的准确性,且该降价耦合方法的计算效率相对于直接CFD/CSD耦合方法提高了1~2个量级,为叶轮机气动弹性参数研究、失谐研究以及多模态耦合计算等提供了便利.

关键词: 叶栅, 气动弹性, 颤振, 降阶模型, 计算流体力学, 耦合方法

Abstract:

As direct numerical simulation of fluid/structure interaction of entire blade row is computation-intensive and time-consuming, this paper presents a reduced order model (ROM)-based coupling method which takes fluid/structure coupling effect into account and provides a significant increase in efficiency of flutter analysis of turbomachinery. This method computes unsteady aerodynamic forces of several blades in time domain by computational fluid dynamics (CFD) technique, and then constructs the reduced order aerodynamic model of entire vibrating cascade with system identification and several assumptions. And finally, this method establishes the aeroelastic model of entire cascade by coupling the reduced order aerodynamic mode with cascade structural dynamic equation in state-space form. Flutter characteristics of STCF4 (Standard Test Configuration 4) and NASA Rotor67 cascade are analyzed by solving eigenvalues of the aeroelastic model. The accuracy of this method is validated by comparing the results of direct computational fluid dynamics/computational structural dynamics (CFD/CSD) coupling method and uncoupled method. The ROM-based coupling method improves computational efficiency by nearly two orders of magnitude compared to direct CFD/CSD coupling method. Besides, this method provides an effective and reliable approach for parameter analysis, mistuning and multi-mode coupling calculation of turbomachinery.

Key words: cascade, aeroelasticity, flutter, reduced ordered model, computational fluid dynamics, coupled method

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