某型发动机高压涡轮叶片叶尖裂纹修复工艺研究  

Repairing Technology of High Pressure Turbine Blade Tip Crack for an Aero-Engine

作　　者：孔令有 于萍[2] 

机构地区：[1]沈阳发动机设计研究所,辽宁沈阳110015 [2]沈阳黎明发动机(集团)有限责任公司,辽宁沈阳110043

出　　处：《航空发动机》2007年第1期49-50,54,共3页Aeroengine

摘　　要：采用激光熔焊法,排除了某型发动机高压涡轮工作叶片叶尖裂纹超标及开口型叶尖裂纹故障。对修理后的叶片进行了热冲击试验考核,考核证明了修复后的高压涡轮工作叶片可满足发动机工作要求。The over- limit and visual cracks occurred in an aero -engine high pressure turbine blade tip were repaired using laser welding. The heat impact test of the repaired blades were conducted. The test results demonstrated that the repairing technology was successful..

关 键 词：航空发动机 高压涡轮叶片 激光熔焊 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]