航空学报 > 2015, Vol. 36 Issue (10): 3305-3315   doi: 10.7527/S1000-6893.2015.0025

失谐叶片轮盘的减缩建模及动力响应预测方法

臧朝平1, 段勇亮1, E. P. PETROV2   

  1. 1. 南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;
    2. 塞克斯大学 工程与信息学院, 布莱顿 BN1 9QT
  • 收稿日期:2014-10-20 修回日期:2014-11-13 出版日期:2015-10-15 发布日期:2015-03-25
  • 通讯作者: 臧朝平, Tel.: 025-84892200-2204 E-mail: c.zang@nuaa.edu.cn E-mail:c.zang@nuaa.edu.cn
  • 作者简介:臧朝平 男, 博士, 教授, 博士生导师。主要研究方向: 航空发动机模型确认, 结构动力学模型修正理论, 结构健康状态监测及破坏监测, 转子振动的连续扫描激光测量, 旋转机械工况监测及故障诊断, 叶盘失谐。 Tel: 025-84892200-2204 E-mail: c.zang@nuaa.edu.cn;段勇亮 男, 硕士研究生。主要研究方向: 航空发动机失谐叶盘结构动力学。 Tel: 025-84892200-2417 E-mail: tracy_duan@nuaa.edu.cn;E.P.PETROV 男, 访问教授。主要研究方向: 叶盘结构动力学, 非线性接触力学。 Tel: +44-0-1273872537 E-mail: y.petrov@sussex.ac.uk
  • 基金资助:

    国家自然科学基金 (11372128, 51175244); 中央高校基本科研业务费专项资金 (NP2013302, NN2012067); 南京航空航天大学研究生创新基地(实验室)开放基金 (kfjj20130204); 先进航空发动机协同创新中心项目

Reduced-order modelling and dynamic response prediction method for mistuned bladed disks

ZANG Chaoping1, DUAN Yongliang1, E. P. PETROV2   

  1. 1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. School of Engineering and Informatics, University of Sussex, Brighton BN1 9QT, United Kingdom
  • Received:2014-10-20 Revised:2014-11-13 Online:2015-10-15 Published:2015-03-25
  • Supported by:

    National Natural Science Foundation of China (11372128, 51175244); The Fundamental Research Funds for the Central Universities (NP2013302, NN2012067); Fundation of Graduate Innovation Center in NUAA (kfjj20130204); Project of Collaborative Innovation Center for Advance Aero-engine

摘要:

为解决高保真失谐叶盘计算量大的问题,提出了一种新的减缩建模及动力响应预测方法。该方法对叶盘单扇区有限元模型进行圆周对称分析,获取谐调叶盘在局部坐标系下的基本模态特性。同时,运用主节点的概念,仅对少量节点进行模态分析,在大大降低矩阵维度的同时获取准确的失谐模态特性。在动力响应预测分析时,利用失谐固有频率点处响应的基本特性,仅选取危险频段内、危险叶片上的危险节点进行响应分析计算,既极大地提高了运算效率,又能够准确地获取叶盘最大受迫响应幅值。实例分析结果表明:相较于传统的有限元方法,该方法中模态分析的求逆过程矩阵维度从150万下降到384,计算所得的前50阶固有频率的精度保持在0.005%以内,最大响应计算过程运算量下降超过99%时,仅存在-0.35%的误差。

关键词: 失谐, 叶盘, 减缩建模, 动力学, 响应预测, 主节点

Abstract:

In order to save the great computation effort for high fidelity mistuned bladed disk, a new reduced-order modelling and dynamic response prediction method for mistuned bladed disks is developed in this paper. Taking full advantage of cyclic symmetry of tuned bladed disk, a sector model is used to provide the primary information about dynamic properties in the local coordinate systems. Just doing model analysis on a small number of nodes utilizing the concept of "active nodes", the dimensions of operation matrices are reduced enormously but the model properties of mistuned structure are preserved with very high accuracy. In the process of dynamic response prediction, the response properties on the natural frequencies can be used for the choice of narrow frequency ranges, dangerous blades and nodes which need to calculate response. The main advantages are its efficiency and accuracy, which allow the high precision maximum forced responses. The results show that compared with traditional finite element method, the inverse matrices in this method are reduced from 1.5 million to 384, but the errors of the first 50 natural frequencies are limited in 0.005%. In addition, the computational complexity of maximum response calculation is lowered by more than 99%, which just produces -0.35% deviation.

Key words: mistuning, bladed disk, reduced-order modelling, dynamic, response prediction, active nodes

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