为了减少航空发动机加力内锥体使用中出现的屈曲失稳故障，保障发动机整机安全，基于线性屈曲理论、有限单元法理论和三维有限元数值仿真技术，开展发动机加力内锥体屈曲分析，获得加力内锥体的临界失稳载荷和屈曲失稳模式，并根据加力内锥体的结构形式和受载特点，提出多个结构改进措施。分析表明：加力内锥体在外压大于内压状态下临界失稳载荷较小，极易出现屈曲失稳，且失稳位移沿周向呈波瓣状分布；整体加厚方案可有效提升临界失稳载荷，但会带来重量的大幅增加，而在失稳变形较大位置增加壁厚的方案为最优改进方案。

In order to reduce the buckling failure of aeroengine afterburner inner cone(AIC) in the use and ensure the safety of the whole engine, basing on the linear buckling theory, finite element theory and threedimensional finite element simulation technology, the buckling analysis of AIC was carried out, the critical bulking loading and bulking mode of AIC were obtain. Several structural improvement measures were proposed according to the AIC′s structure form and loading characteristics. The results showed that the critical bulking load was smaller and AIC was easy to suffer from buckling when the external pressure was greater than the internal pressure, the bulking displacement mode was distributed in a lobe shape along the circumferential direction. The overall thickening scheme could effectively increase the critical bulking load at the cost of increasing weight, the thickening scheme in the position of large bulking deformation was the optimum scheme.

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山西省关键核心技术和共性技术研发攻关专项项目资助(2020XXX017)；山西省基础研究计划（青年科学研究项目202203021222129）