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提出一种分段解析法,推导给定变厚度涡轮盘内外缘加热能量下涡轮盘的温度分布与应力分布,从而建立起以能量转移系数表示的涡轮盘能量分布与温度分布及应力分布之间的直接关联.该关联应用于某型航空发动机低压涡轮盘,并通过与数值模拟对比,结果显示:温度与应力的理论分析结果与数值模拟结果吻合较好,最大相对偏差分别为2%与13%;等边界热流量条件下,随着能量转移系数的增大,涡轮盘内缘温度增大,外缘温度减小,涡轮盘等效应力水平降低,最大等效应力减小.分段解析法获得的能量分布与应力分布关联的准确性与可行性得到了验证.
A piecewise analytical method was proposed to derive the temperature distribution and the stress distribution of the turbine disc under the heating energy inside and outside the given variable thickness turbine disc so as to establish the relationship between the energy distribution and the temperature distribution and the stress distribution of the turbine disc represented by the energy transfer coefficient The results show that the theoretical analysis results of temperature and stress are in good agreement with the numerical simulation results and the maximum relative deviations are 2% and 13%, respectively %; Under the condition of equal boundary heat flux, with the increase of energy transfer coefficient, the inner temperature of turbine disk increases, the outer temperature decreases, the equivalent stress of turbine disk decreases and the maximum equivalent stress decreases. The accuracy and feasibility of the correlation between energy distribution and stress distribution obtained by the method have been verified.