摘要
对断裂叶片进行材质和断口等综合分析,确认高压压气机Ⅰ、Ⅱ级叶片断裂的特征和失效模式,明确叶片断裂失效与材料的力学性能等冶金因素无关。结果显示:高压压气机Ⅰ级叶片断裂为疲劳断裂,为首断件和肇事件;Ⅱ级叶盘所有叶片均为大应力作用下的疲劳断裂,为受害件。Ⅰ级叶盘叶片断裂与承受较大的共振应力有关,属于结构设计问题。进一步的分析表明,压气机Ⅰ级叶盘叶片叶型厚度超差,使得K=3激起的一阶弯曲共振转速更靠近慢车转速区域。疲劳断裂叶片在裂纹萌生处存在明显的横向加工痕迹,降低了疲劳性能。叶片表面较明显的加工损伤对Ⅰ级转子叶片断裂起到一定的促进作用。
The fracture characteristics and failure modes of the first-and second-stage blades in a high-pressure compressor were confirmed by comprehensive analysis on the material and fracture surface of the fractured blades.The results show that the fracture of the blades has nothing to do with the material.The first-stage blades of the high-pressure compressor first fractured,and their failure mode is fatigue fracture.The failure mode of all the second-stage blades is fatigue fracture by larger stress,so they are victims.The fracture of the first-stage blades is mainly related to larger resonance stress,which belongs to structural design problem.Further analysis shows that the thickness of the first-stage blades is excessive,making the first-order bending resonance speed caused by K=3 closer to the speed range of slow car.There are obvious transverse machining marks near the crack source of the fatigue fracture blades,which reduced the fatigue performance.The obvious machining damage on the blade surface promoted the fracture of the first-stage blades.
作者
李彦
都建京
陈星
刘新灵
李佳佳
LI Yan;DU Jian-jing;CHEN Xing;LIU Xin-ling;LI Jia-jia(AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation,Beijing 100095,China;AECC Key Laboratory of Science and Technology on Aeronautical Materials Testing and Evaluation,Beijing 100095,China;AECC Failure Analysis Center,Beijing 100095,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)
出处
《失效分析与预防》
2019年第3期188-192,共5页
Failure Analysis and Prevention
