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通过对某型航空发动机高压涡轮盘进行弹塑性有限元分析,计算涡轮盘在主次循环作用下的低循环疲劳寿命和寿命的概率分布,从而对涡轮盘在某飞行科目中的寿命损伤进行分析。对涡轮盘进行热分析;并对载荷谱进行分析处理,得出对涡轮盘损伤影响较大的主次循环和相应载荷谱;再对涡轮盘进行弹塑性分析,得到危险点处的应力、应变,计算涡轮盘确定性寿命和寿命的概率分布;利用线性损伤累积理论,得到涡轮盘在单次飞行和千小时飞行下的总损伤。
Through the elasto-plastic finite element analysis of a high-pressure turbine disk of aeroengine, the probability distribution of low-cycle fatigue life and life of turbine disk under primary and secondary cycles is calculated to analyze the life-span damage of turbine disk in a flight subject . The thermal analysis of the turbine disk was carried out. The main and secondary cycles and the corresponding load spectra, which had a great influence on the turbine disk damage, were obtained through the analysis and processing of the load spectrum. Then the elastoplastic analysis of the turbine disk was carried out to obtain the stress and strain at the dangerous point , Calculate the probability distribution of the deterministic life span and life span of the turbine disk, and use the linear damage accumulation theory to get the total damage of the turbine disk under the single flight and thousands of hours flight.