【摘要】 火箭发动机涡轮盘工作在高温、高转速及恶劣的振动环境中 ,并承受着较大气动力作用 ,是发动机的关键组合件 ,涡轮盘的失效破坏将严重影响发动机的正常工作 ,甚至带来灾难性的后果。针对某火箭发动机涡轮盘在热试车中出现的裂纹故障 ,进行全面的分析 ,准确定位故障类型 ,以试验和计算分析给出合理的故障原因 ,重点是在疲劳分析方面所做的工作 ,包括振动模拟试验、疲劳强度计算 ,并根据疲劳强度分析结果提出改进方案。结果表明原结构圆角处应力集中明显 ,静态应力值水平高 ,在发生耦合振动后 ,涡轮盘出现疲劳裂纹 ,最终发生低周大应力破坏。试验和计算表明 ,采用改进方案可有效降低R圆角处的应力集中 ,明显提高疲劳强度。对采用改进方案后的涡轮盘发动机进行了多次热试车 ,证实改进后的结构未发生耦合振动 ,未发现疲劳裂纹 ,改进方案是可行的。更多还原

【Abstract】 Turbine disk is a very key component in rocket engine operating in high temperature, high rotating speed and hostile vibration environment, as well as experiencing great aerodynamic loads. Its failure will lead to unsteady operation of rocket engine, and sometime cause catastrophic consequence. The damage analysis of cracked turbine disk in the rocket engine is described. From a series of analyses, the causes of failure were reasoned through calculation and experiments, fatigue analyses which include stimulating vibration test and fatigue strength calculation were emphasized. The results show that high stress concentration exists in the “R fillet"of turbine disk resulting a great static stress level. When high amplitude resonance occurs, it may cause cracking damage of turbine disk. The improvement design can effectively decrease stress concentration and also increase the fatigue strength of the area. The following hot fire tests demonstrated the success of the improved design.更多还原