航空发动机燃油分管断裂故障分析  

Failure analysis on fracture of fuel nozzle supply tube for an aeroengine

作　　者：田中礼 王少波 曹阳 柴昕 李春野 边际 朱宇 TIAN Zhong-li;WANG Shao-bo;CAO Yang;CHAI Xin;LI Chun-ye;BIAN Ji;ZHU Yu(Department of Combustor Design,AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所燃烧设计研究室,沈阳110015

出　　处：《沈阳航空航天大学学报》2022年第2期14-20,共7页Journal of Shenyang Aerospace University

基　　金：国家科技重大专项(项目编号:2017-Ⅲ-002-0026)。

摘　　要：某型航空发动机主燃烧室燃油分管锥面接嘴台阶根部在外场试飞过程中发生了断裂故障。为了查明故障原因,提高主燃烧室燃油分管使用的可靠性和安全性,对燃油分管故障件进行了故障分析。分析结果表明:主燃烧室燃油分管出现断裂的主要原因是由装配带来的较大初始应力所引起。在发动机工作中,装配应力和热膨胀应力叠加后导致较大的静应力,随后燃油分管在发动机振动条件下产生疲劳断裂。针对故障原因,制定了结构改进、工艺改进、装配工艺完善等改进措施,降低了装配应力,有效地避免了此类故障再次发生,从而使该类故障归零。A fracture failure at root of fuel nozzle supply tube of main combustor for an aeroengine occurred during flight test.In order to figure out the failure cause and improve reliability and safety of the fuel nozzle supply tube,failure analysis was carried out.The results show that the main reason of the fracture was the large initial stress caused by assembly.During engine operation,superposition of the assembly stress and the thermal expansion stress led to a large static stress,which finally resulted in fatigue fracture under the engine vibration.According to the failure cause,various improvement measures such as structural improvement,technology improvement,assembly process improvement and other improvement measures were adopted,which greatly reduced the assembly stress and effectively avoided recurrence of the same kind of failure.Then the fault return-to-zero was completed.

关 键 词：燃油分管 断裂 故障分析 主燃烧室 航空发动机 

分 类 号：V263.6[航空宇航科学与技术—航空宇航制造工程]