摘要
某飞机在起飞时尾喷管发生喷火,其燃气涡轮一、二级叶片断裂,在尾喷管及相关机匣内表面存在大量的金属附着物。对断裂的叶片进行断口宏微观观察、金相组织检验。结果表明:燃气涡轮一、二级叶片断口为沿晶脆性断口,高温区组织出现过热,局部过烧,导致叶片断裂的原因是发动机在超温状态下工作。
The tailpipe nozzle of an aircraft caught fire during taking off,and it was found that both its first-level and second-level gas-turbine blades had fractured.A lot of attachments existed at the internal surface of the tailpipe nozzle.In order to find out the cause for the failure,macro and micro observation,energy spectrum analysis,and metallurgical structure examination were carried out.The results show that the fracture of the blades is intergranular brittle fracture.The main cause for the fracture of the blades is overheating and overburning of the high temperature affected zones,which was caused by over temperature work of the engine.
出处
《失效分析与预防》
2010年第4期252-256,共5页
Failure Analysis and Prevention
关键词
燃气涡轮叶片
高温合金
超温
过烧组织
gas-turbine blade
superalloy
over temperature
overburned structure
