摘要
在修理某发动机时,发现很多高压涡轮叶片叶尖出现超出使用技术条件规定的裂纹,导致大量叶片报废,分析认为裂纹的产生是"钉扎效应"的结果,而且是先腐蚀后开裂的。为修复这些高压涡轮叶片,缩短发动机修理周期、降低修理成本,采用高钨、锰含量的镍基超合金作为补焊材料,同时采用固体激光脉冲焊接的工艺方法对产生叶尖裂纹的高压涡轮叶片进行了修复。修复后的高压涡轮叶片经去除应力、热处理等工序步骤后,通过了热冲击试验、整机试车考核和装机使用,说明采用该种修理工艺修复的高压涡轮叶片可以满足装机使用要求。
A lot of cracks occurred in high pressure turbine blade tip during the repair of engine. The cracks are beyond the limit technical conditions, and lead to a large number of blade scrap. Analysis shows that the cracks are the results of ＂pinning effect＂, and corroded first and then crazed. In order to reduce the repair cycle and cost, the repair of high pressure turbine tip cracks are completed by solid state laser pulse welding process using nickel bossed superalloy with high content of Tungsten, and Manganese as weld material. After removing the stress and heat treatment, the high pressure turbine blade repaired were demonstrated by thermal shock test, engine test and actual flight test. The results show that the repair technique can meet the operation requirement.
出处
《航空发动机》
2014年第4期79-83,共5页
Aeroengine
关键词
高压涡轮叶片
叶尖裂纹
激光焊接
航空发动机
修复
high-pressure turbine blade
blade tip cracking
laser welding
aeroengine
repair
