某航空发动机压气机转子叶片腐蚀断裂分析  

Corrosion Fracture Analysis of Compressor Blade Rotor in An Aeroengine

作　　者：张晓晶 古远兴 孙海鹤 郝永振 ZHANG Xiaojing;GU Yuanxing;SUN Haihe;HAO Yongzhen(AECC Sichuan Gas Turbine Establishment,Chengdu Sichuan 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川成都610500

出　　处：《海军航空大学学报》2024年第6期707-714,共8页Journal of Naval Aviation University

摘　　要：针对某涡扇发动机试车时发生的压气机转子叶片裂纹故障,文章通过分析叶片的强度和振动特性,得出叶片在工作时存在共振的风险;采用非接触测量方法对叶片进行了振动测量,获得了无腐蚀坑转子叶片的振动应力。通过开展叶片高周疲劳试验,验证了非腐蚀状态叶片的工作可靠性;利用Pairs公式反推了腐蚀状态下叶片的裂纹扩展门槛值,分析了叶片开裂的原因。研究表明,断裂的主要原因是,首先叶片形成腐蚀坑,之后在高循环交变载荷的作用下腐蚀疲劳失效。文章重点从工艺角度改进,控制了材料回火温度范围,增加了叶片表面渗铝工艺,有效预防了叶片断裂失效的发生,提高了叶片工作可靠性。In view of the crack failure of compressor blade in turbofan engine during the test,the strength and vibration characteristic of the blade are analyzed,and it found that blade is in resonance during working.It is abtained that vibration stress of blade without conrrosive pit are measured by non-contact measurement,and it is verified that operation reliability of non-corroded blade by high-cycle fatigue tests of blade.Fatigue crack growth threshold of blade under corrosion is estimated with Pairs,and the causes of blade cracking are analyzed.The main reason of fracture is that corrosion pit is formed and the blade is failure under the action of high cyclic.Focus on the improvement from the manufacturing process,the temperature range of tempering is controlled,aluminizing process of the blade surface is increased,and the blade fracture is prevented effectively,the working reliability of the blade is improved.

关 键 词：叶片 腐蚀疲劳 缺口 振动 应力强度因子 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]