Abstract: Aeroengine casings were typical thin-walled frame structure, aiming at complicated impact loads due to axial and circum-torsional impacts by turbine rotors caused by shaft breaks, the numerical simulation models were established involving key components of turbine rotors and exhaust casings. On the basis of the complicated impact loads and energy dissipations of the exhaust casings in the simulation results, the dynamic responses of complicated impact loads and energy dissipations in the processes of complicated impacts were obtained. It is pointed out that the initial rotation velocity has little influences on impact loads and energy dissipations under the conditions of certain axial forces in the term of the complex movements of turbine rotors. Furthermore, the relative motion relation between the turbine rotor and the exhaust casing was converted. The analysis results show that the impact load and energy dissipation results after conversion remain highly similar to those before conversion. In the subsequent equivalent test methods, these conclusions might be used as a reference for simplifying the structural design of test bed.

Key words: turbine rotor, exhaust casing, axial containment, impact load, equivalent test

摘要： 航空发动机机匣属于典型薄壁框架结构，针对断轴后其承受的由涡轮转子的轴向冲击与周向扭转冲击构成的复杂冲击载荷，建立了包含涡轮转子与排气机匣等关键部件的数值仿真模型，以仿真结果中排气机匣的复杂冲击载荷与能量耗散为切入点，获得了复杂冲击过程中二者的动态响应；指出在涡轮转子的高速旋转与轴向移动复合运动因素中，初始转速对冲击载荷与能量耗散无明显影响；进一步转换涡轮转子与排气机匣的相对运动关系，分析结果表明，转换后的冲击载荷和能量耗散结果与转换前保持高度相似。在后续的等效试验方法中，这些研究结论可成为简化试验台结构设计的参考。

关键词: 涡轮转子, 排气机匣, 轴向包容, 冲击载荷, 等效试验