为了研究热-流-固耦合下航空叶片的变形机理，通过建立精细的单向与双向热-流-固耦合模型，对叶片在不同环境温度（进口总温）下的变形规律和变形机理进行了深入探讨。研究结果表明：热-流-固耦合作用对叶片的变形具有显著影响，其中温度和压力是主要影响因素；在双向热流固耦合时，随着环境温度的升高叶片的最大变形从293K时的0.4770mm增大到1573K时的2.1051mm。环境温度为293K时，叶片的应力应变主要集中在叶片根部，且在叶片前缘和后缘出现最大等效应力为820.21MPa以及最大等效弹性应变为0.0056；单向和双向热流固耦合在环境温度为293K时仿真得到的叶片最大变形以及最大等效应力最为接近，分别为0.3976mm、0.4770mm和795.53MPa、820.21MPa，其相对于双向耦合的偏差分别为16.64%和3.01%；随着环境温度的升高单向和双向热流固耦合得到叶片最大变形的差值越大。

In order to study the deformation mechanism of aviation blades under thermal-fluid-solid coupling, the deformation rule and deformation mechanism of blades under different ambient temperature (total inlet temperature) were deeply discussed by establishing fine unidirectional and bidirectional thermal-fluid-solid coupling models. The results show that thermal-fluid-solid coupling has a significant effect on blade deformation, and temperature and pressure are the main influencing factors. The maximum blade deformation increases from 0.4770mm at 293K to 2.1051mm at 1573K with the increase of ambient temperature. When the ambient temperature is 293K, the stress-strain of the blade is mainly concentrated at the root of the blade, and the maximum equivalent stress and the maximum equivalent elastic strain are 820.21MPa and 0.0056 respectively at the leading and trailing edges of the blade. When the ambient temperature is 293K, the maximum blade deformation and the maximum equivalent stress obtained by simulation are the closest, which are 0.3976mm, 0.4770mm and 795.53MPa and 820.21MPa, respectively, and the deviations relative to the two-way coupling are 16.64% and 3.01%, respectively. With the increase of ambient temperature, the difference of maximum blade deformation between unidirectional and bidirectional thermal fluid-structure coupling increases.