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为了更精确地研究航空发动机叶片通过共振转速区发生短时间共振时的可靠性,在考虑共因失效(由振动一种因素引起的叶片变形和应力失效)的基础上,提出了航空发动机振动可靠性分析方法的双重响应面法。通过模态分析和谐响应分析得到叶片的最大变形和最大应力,选取密度、转速和气动力为输入变量,变形和应力为输出响应,建立了叶片最大变形和最大应力的响应面数学模型,在考虑转速、气动力、材料密度的基础上,得出了叶片的可靠性。分析结果表明:当叶片的允许变形量均值为2.45mm,方差为0.0368 mm,许用应力均值为540MPa,方差为8.1 MPa时,可靠性概率为99.14%。通过与Monte-Carlo法进行比较,验证了双重响应面方法在叶片发生短时间共振中的可行性和有效性。
In order to study the reliability of aeroengine blades in short time resonance through the resonance speed region more accurately, based on the consideration of common cause failure (blade deformation and stress failure caused by a factor of vibration), aeroengine vibration is proposed Double response surface method of sexual analysis method. The maximum deformation and the maximum stress of the blade are obtained through the modal analysis of harmonic response analysis. The density, rotation speed and aerodynamic force are taken as the input variables, and the deformation and stress are the output responses. The mathematical model of the response surface of the maximum deformation and the maximum stress is established. , Aerodynamic force, material density, based on the obtained blade reliability. The analysis results show that the reliability probability is 99.14% when the average allowable deformation of blade is 2.45mm, the variance is 0.0368mm, the allowable stress is 540MPa and the variance is 8.1MPa. By comparing with the Monte-Carlo method, the feasibility and effectiveness of the double response surface method in short-time blade resonance are verified.