【摘要】 基于振动设计理论,考虑失谐叶盘系统激振频率和模态频率的相关性,提出了1种航空发动机失谐叶盘系统避共振可靠度的计算方法。通过确定性分析和概率分析说明了失谐会增加叶盘系统避共振难度,并得到叶盘系统模态频率的概率分布特性。在此基础上,运用所提出方法,拟合得到失谐叶盘系统的避共振可靠度响应面,进而用该响应面计算不同结构谐波系数下失谐叶盘系统避共振可靠度。将计算结果与蒙特卡洛法及未考虑激振频率和模态频率相关性的传统方法的结果进行对比,验证了所提出方法在失谐叶盘系统避共振可靠性分析中的准确性。更多还原

【Abstract】 Based on the theory of vibration design and considering the correlation between excitation frequency and modal frequency of the mistuned bladed disk assemblies system,a method for calculating the anti-resonance reliability of the aeroengine mistuned bladed disk assemblies system was proposed.Through deterministic analysis and probabilistic analysis,it was shown that mistuned would increase the difficulty of anti-resonancebladed disk assemblies system and the probability distribution of the modal frequency of the bladed disk assemblies system was obtained. According to the proposed method, the reliability response surface of anti-resonance of mistuned bladed disk system was obtained. Finally,the reliability of anti-resonance of mistuned bladed disk system under different structural harmonic coefficient was calculated by the response surface.The calculated results were compared with those obtained by Monte Carlo Method and traditional methods without considering the correlation between excitation frequency and modal frequency. The accuracy of the proposed method in the analysis of the anti-resonance reliability of the aeroengine mistuned bladed disk assemblies systemwas verified.更多还原