某航空发动机卡箍断裂故障分析
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摘要
针对某航空发动机在试车过程中风扇机匣安装边上用于固定管路的多处卡箍发生的断裂故障,通过对卡箍故障件进行断口分析和设计复查等,确定了卡箍断裂发生的原因:在设计状态下,卡箍上、下瓣之间装配夹角较大,在螺栓拧紧过程中,造成卡箍结构故障位置产生较大的初始局部应力,在较大的振动环境下导致综合应力增大,由于故障位置结构强度储备不足,从而发生高周疲劳断裂。通过对卡箍结构采取加装2 mm厚钢垫、降低静应力等改进措施优化设计,降低了其静应力,提高了其强度储备,有效避免此类故障再次发生。
In view of the fracture fault of multiple clamps on the side of fan casing installation used for fixed pipes during the test run of an aeroengine,the fracture surface analysis and design review of the fauit clamps parts were carried out,and the reason of clamps fracture was identified. In the design state,the angle between the upper and lower lobes of the clamps was large. In the process of tightening bolt,the fault position of clamp structure was caused by large initial local stress. Under the larger vibration environment,the comprehensive stress increases,and the high cycle fatigue fracture occured because the strength reserve of the fault location structure was insufficient. The optimum design of clamp structure was adopted by adding 2 mm thick steel cushion and reducing static stress. Then the static stress was reduced,the strength reserve was increased,and this kind of fault was prevented from happening again.
In view of the fracture fault of multiple clamps on the side of fan casing installation used for fixed pipes during the test run of an aeroengine,the fracture surface analysis and design review of the fauit clamps parts were carried out,and the reason of clamps fracture was identified. In the design state,the angle between the upper and lower lobes of the clamps was large. In the process of tightening bolt,the fault position of clamp structure was caused by large initial local stress. Under the larger vibration environment,the comprehensive stress increases,and the high cycle fatigue fracture occured because the strength reserve of the fault location structure was insufficient. The optimum design of clamp structure was adopted by adding 2 mm thick steel cushion and reducing static stress. Then the static stress was reduced,the strength reserve was increased,and this kind of fault was prevented from happening again.
引文
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[17]王少飞,温志勋,郜玉芬.配合间隙对涡轮叶片榫头/榫槽接触的影响[J].推进技术,2015,36(1):112-118.WANG Shaofei,WEN Zhixun,GAO Yufen. Effects of contact gap on contact properties of turbine blade tenon/mortise[J].Journal of Propulsion Technology,2015,36(1):112-118.(in Chinese)
[18]张春华.航空发动机管路断裂分析及其结构优化设计[D].大连:大连理工大学,2016.ZHANG Chunhua. Fracture analysis and structural optimization design of aero-engine pipe[D].Dalian:Dalian University of Technology,2016.(in Chinese)
[2]刘伟,曹刚,翟红波.发动机管路卡箍位置动力灵敏度分析与优化设计[J].航空动力学报,2012,27(12):2756-2762.LIU Wei,CAO Gang,ZHAI Hongbo. Sensitivity analysis and dynamic optimization design of supports'positions for engine pipelines[J].Journal of Aerospace Power,2012,27(12):2756-2762.(in Chinese)
[3]李鑫,王少萍.基于卡箍优化布局的飞机液压管路减振分析[J].振动与冲击,2013,32(1):14-20.LI Xin,WANG Shaoping. Vibration control analysis for hydraulic pipelines in an aircraft based on optimized clamp layout[J]. Journal of Vibration and Shock,2013,32(1):14-20.(in Chinese)
[4]郭家良,王维,贾文强.航空发动机外部管路调频方法研究[J].航空发动机,2017,43(6):33-38.GUO Jialiang,WANG Wei,JIA Wenqiang. Investigation on frequency modulation methods of aeroengine external pipe[J]. Aeroengine,2017,43(6):33-38.(in Chinese)
[5]肖伟,高永丹.发动机滑油弯管卡箍衬垫故障分析[J].失效分析与预防,2012,7(4):248-252.XIAO Wei,GAO Yongdan. Failure analysis of clamp of bending tube in engine[J]. Failure Analysis and Prevention,2012,7(4):248-252.(in Chinese)
[6]李刚,李明.铝合金-丁腈橡胶航空带垫卡箍典型环境损伤研究[J].装备环境工程,2017,14(6):65-70.LI Gang, LI Ming. Damage on aluminum alloy-nitrile rubber aeronautic clamp with cushion in typical environments[J].Equipment Environment Engineering,2017,14(6):65-70.(in Chinese)
[7]周宁波,郑贤中,郑晓敏,等.预紧卡箍式快开结构的安全强度分析[J].武汉工程大学学报,2012,34(4):53-58.ZHOU Ningbo,ZHENG Xianzhong, ZHENG Xiaomin, et al. Safety strength of preloaded clamp quick-opening structure[J].J.Wuhan Inst.Tech. 2012,34(4):53-58.(in Chinese)
[8]刘国库,刘冬.压气机转子叶片叶根断裂故障分析[J].航空发动机,2016,42(3):93-97.LIU Guoku,LIU Dong. Fracture failure analysis for blade root of compressor[J]. Aeroengine,2016,42(3):93-97.(in Chinese)
[9]佟文伟.某燃气涡轮发动机螺栓断裂失效分析[J].航空发动机,2013,39(4):67-71.TONG Wenwei. Fracture failure analysis of bolt in a gas turbine engine[J]. Aeroengine,2013,39(4):67-71.(in Chinese)
[10]中国航空材料手册编辑委员会.中国航空材料手册:第1卷[M].北京:中国标准出版社,1988:658-675.Editorial Board of China Aviation Materials Handbook. China aviation materials handbook:Vol.1[M]. Beijing:Standards Press of China,1988:658-675.(in Chinese)
[11]马英广.发动机螺栓拧紧技术的研究[D].哈尔滨:哈尔滨工程大学,2006.MA Yingguang. Research on technology of tightening bolts on engine[D].Harbin:Harbin Engineering University,2006.(in Chinese)
[12]孙国峰.基于超声波技术的螺栓紧固轴力测量应用研究[D].杭州:浙江工业大学,2012.SUN Guofeng. Research on axis force of bolt tightening based on the ultrasonic measurement technology[D].Hangzhou:Zhejiang University of Technology,2012.(in Chinese)
[13]浦广益.ANSYS Workbench基础教程与实例详解[M]. 2版.北京:中国水利水电出版社,2013:48-242.PU Guangyi. ANSYS workbench basic tutorial[M]. 2nd ed. Beijing:China Water Power Press,2013:48-242.(in Chinese)
[14]王晶,陈果,郑其辉.飞机液压管道初始装配应力仿真[J].航空计算技术,2012,42(6):54-57.WANG Jing,CHEN Guo,ZHENG Qihui. Simulation of initial assembly stress for aircraft hydraulic pipeline[J]. Aeronautical Computing Technique,2012,42(6):54-57.(in Chinese)
[15]王桂华,刘海年,张大义.航空发动机成附件振动环境试验剖面确定方法研究[J].推进技术,2013,34(8):1101-1107.WANG Guihua,LIU Hainian,ZHANG Dayi. Study on formulating method for vibration environment test profiles of aero-engine accessories[J]. Journal of Propulsion Technology,2013,34(8):1101-1107.(in Chinese)
[16]江平,李刚,陈青兰.航空发动机附件传动齿轮辐板动应力测试技术[J].航空动力学报,2016,31(10):2536-2543.JIANG Ping,LI Gang,CHEN Qinglan. Dynamic strain monitoring technique for the rim of cylinder gear in the aero-engine[J]. Journal of Aerospace Power,2016,31(10):2536-2543.(in Chinese)
[17]王少飞,温志勋,郜玉芬.配合间隙对涡轮叶片榫头/榫槽接触的影响[J].推进技术,2015,36(1):112-118.WANG Shaofei,WEN Zhixun,GAO Yufen. Effects of contact gap on contact properties of turbine blade tenon/mortise[J].Journal of Propulsion Technology,2015,36(1):112-118.(in Chinese)
[18]张春华.航空发动机管路断裂分析及其结构优化设计[D].大连:大连理工大学,2016.ZHANG Chunhua. Fracture analysis and structural optimization design of aero-engine pipe[D].Dalian:Dalian University of Technology,2016.(in Chinese)