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 引用本文: 张陈安 张伟伟 叶正寅 刘锋. 一种高效的叶轮机叶片气动阻尼计算方法[J]. 力学学报, 2011, 43(5): 826-833.
Chen-An Zhang Weiwei Zhang Zhengyin Ye Feng Liu. An efficient method on aerodynamic damping coefficient calculation for turbomachinery[J]. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(5): 826-833.
 Citation: Chen-An Zhang Weiwei Zhang Zhengyin Ye Feng Liu. An efficient method on aerodynamic damping coefficient calculation for turbomachinery[J]. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(5): 826-833.

## An efficient method on aerodynamic damping coefficient calculation for turbomachinery

• 摘要: 运用叠加原理, 发展了一种可以运用于小振幅运动的叶轮机叶片非定常气动力降阶模型, 并将该模型与传统的能量法相结合, 提出了一种叶轮机叶片气动阻尼的高效求解方法. 运用该方法求解叶轮机叶片的气动阻尼系数, 对某个频率、某个模态只需要进行一次非定常计算, 就可以求出所有叶间振动相角下的气动阻尼系数, 提高了气动阻尼的求解效率. 在STCF4和NASA Rotor67两个算例上运用非定常雷诺平均N-S(RANS)方程和提出的降阶模型进行了对比计算.算例表明, 在小振幅下该方法的计算结果与RANS方程计算得到的气动阻尼系数能很好地吻合, 而计算效率相比多通道非定常RANS方程计算提升了近一个数量级, 并且该方法还可以运用于有失谐情况的颤振分析, 在工程上有较高的应用价值.

Abstract: It is always difficult to perform aeroelastic analysis onturbomachinery efficiently and precisely due to the complexity of the flowfield and structures. The authors develop an unsteady aerodynamicReduced-Order-Model (ROM) which can be used on small amplitude vibratingblades of turbomachinery. Based on this ROM and classic energy method, anefficient method on aerodynamic damping coefficient calculation forturbomachinery is introduced. With this method, only one unsteady CFDcomputation is needed to calculate the aerodynamic damping coefficients atall Inter Blade Phase Angles (IBPA) under one specific modal and frequency.The aeroelastic characteristics of STCF4 and NASA Rotor 67 are analyzed byusing this ROM with classic energy method. The numerical results indicatethat the aerodynamic damping coefficients attained by ROM and unsteady RANSmethod agree well with each other in the condition of small amplitude ofvibration. The efficiency is improved by almost 10 times than multi-passagesRANS method. In addition, this ROM can be used in aeroelastic analysis withmistuning effects.

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