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对Morrow修正公式中的疲劳强度系数和疲劳强度指数进行修正,建立了涡轮叶片低周疲劳寿命预测模型.利用有限元软件ANSYS对涡轮叶片进行热力耦合计算,得到了涡轮叶片在离心、温度及气动三种载荷联合作用下的应力应变分布规律.应用所提出的低周疲劳寿命预测模型和蠕变持久方程,对在叶身上选取的5个考核点进行了疲劳/蠕变寿命预测.结果表明:叶片寿命为13 114次工作循环,叶片进气面根部的寿命最小,应为涡轮叶片检查和维修的重点部位.
The fatigue strength coefficient and fatigue strength index in Morrow correction formula are corrected and the prediction model of low-cycle fatigue life of turbine blade is established.Using finite element software ANSYS to calculate the thermal coupling of turbine blade, the centrifugal force, temperature and aerodynamic Stress and strain under the combined action of three kinds of loads.The prediction of fatigue / creep life of five test points selected from the leaves was carried out by using the proposed low cycle fatigue life prediction model and the creep-lasting equation.The results showed that: The blade life is 13 114 working cycles, and the life span of the root of the blade inlet is the smallest. It should be the key part of the turbine blade inspection and maintenance.