中文摘要：

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.

英文摘要：

A segmented theoretical method was proposed to derive the temperature and stress distributions of a variable thickness turbine disk under given heating energy on the inner and outer rims,and the correlation between the energy distributions presented by the energy transfer coefficient,and the temperature/stress distributions of the turbine disk was established.By applying the correlation to an aero-engine low pressure turbine disk and comparing the temperature and stress distributions with those obtained from numerical simulation,the results from these two methods show a good agreement;the relative deviations of the temperature and stress distributions are no more than 2%and 13%,respectively;under constant boundary heat flow condition,the temperature of the inner rim increases while that of the outer rim decreases;both the overall equivalent stress level and the maximum equivalent stress of the turbine disk decline with the increase of the energy transfer coefficient.The above results validate that the correlation between the energy and stress distributions obtained from the segmented theoretical method proposed is feasible and correct.