作　　者： (李佳佳）; (何爱杰）; (钟燕）; (刘丽玉）;

机构地区： 中国航发四川燃气涡轮研究院,成都610500

出　　处： 《燃气涡轮试验与研究》 2017年第4期28-33,共6页

摘　　要： 针对K417G合金铸造涡轮整体叶盘在发动机试车考核中出现的叶片裂纹问题,基于裂纹叶片断口宏观、微观分析及低倍组织检查结果,开展了粗晶铸造和表面细晶铸造试样的力学性能对比测试及叶片共振转速分析。结果表明,整体叶盘叶片裂纹产生的主要原因是高压涡轮导叶数24激起的3阶共振,同时粗晶铸造和叶片根部厚度偏薄也降低了叶片的疲劳抗力。为此,采取改变高压涡轮导叶数、增加叶片根部厚度和改用表面细晶铸造工艺等措施,有效避开了叶片危险共振并提高了叶片的疲劳抗力。经后续试验验证考核,叶片采取上述措施后不再出现裂纹问题。 Blade crack was found during the trial run and performance test of K417G high-pressure turbine blisk.Based on the investigation on the fracture surface and macrostructure of the crack blade,analysis of blade resonant speed and the mechanical property test of K417G surface grain refinement process and conventional casting were studied.The analysis results show that the main reason of blade crack is the 3^(rd) order resonances caused by the number of guide blades.Meanwhile,conventional casting and the lower thickness of blade root caused the decreasing of fatigue resistance.In order to avoid the dangerous resonant speed and increase the fatigue resistance of blade,the methods of changing the number of guide blade,increasing the thickness of blade root and using surface grain refinement process were adopted.The verification experiments indicate that the blade crack does not occur after that.

关 键 词： 航空发动机 涡轮整体叶盘 裂纹 共振 故障分析 表面细晶工艺 粗晶铸造工艺 试验验证