A New Reduced Order Modeling for Stability and Forced Response Analysis of Aero-Coupled Blades Considering Various Mode Families
A New Reduced Order Modeling for Stability and Forced Response Analysis of Aero-Coupled Blades Considering Various Mode Families
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考虑各种模态族的气动耦合叶片稳定性和受迫响应分析的新降阶模型
DOI：
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发表时间：
2010
期刊：
影响因子：
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通讯作者：
H. Mårtensson
中科院分区：
文献类型：
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作者：
M. Mayorca;D. Vogt;T. Fransson;H. Mårtensson
本文介绍了一种考虑各种模态族相互作用的气动耦合叶片稳定性和强迫响应分析新方法的描述和应用。这种方法被称为多模态最小二乘法，它考虑了叶片在不同模态形族下运动所产生的非定常力，并通过最小二乘（L2）近似计算了气动矩阵。这种方法可以预测模族与结构、气动和力失谐能力的相互作用。为了减小计算域，采用了投影技术。介绍了该方法在高负荷跨声速压气机叶片调谐和结构失谐强迫响应及稳定性分析中的应用。考虑结构失谐时，受失谐引起的气动阻尼变化影响较大。当阻尼源主要为气动源时，不考虑气动耦合的结构失谐分析可能导致响应估计过高或过低。由于失谐导致的频率分裂会导致模族之间的相互作用，因为它们的频率分离减少了。该方法的优点是捕获了模族相互作用对气动阻尼和强迫响应的影响，而不局限于单模族。
This paper presents the description and application of a new method for stability and forced response analyses of aerodynamically coupled blades considering the interaction of various mode families. The method, here referred as multimode least square, considers the unsteady forces due to the blade motion at different modes shape families and calculates the aerodynamic matrixes by means of a least square (L2 ) approximations. This approach permits the prediction of mode families’ interaction with capabilities of structural, aerodynamic and force mistuning. A projection technique is implemented in order to reduce the computational domain. Application of the method on tuned and structural mistuned forced response and stability analyses is presented on a highly loaded transonic compressor blade. When considering structural mistuning the forced response amplitude magnification is highly affected by the change in aerodynamic damping due to mistuning. Analyses of structural mistuning without aerodynamic coupling might result in over-estimated or under-estimated response when the source of damping is mainly aerodynamic. The frequency split due to mistuning can cause that mode families’ interact due to reducing their frequencies separation. The advantage of the present method is that the effect of mode family interaction on aerodynamic damping and forced response is captured not being restricted to single mode families.