发动机液氧冷却导管断裂失效分析  

Fracture Failure Analysis of A Liquid Oxygen Cooling Pipe for Engine

作　　者：宋亚轻 周丽兵 王柯 王婷[1] 王振 SONG Yaqing;ZHOU Libing;WANG Ke;WANG Ting;WANG Zhen(Xi′an Aerospace Propulsion Institute,Xi′an,710100;Academy of Aerospace Propulsion Technology,Xi′an,710025)

机构地区：[1]西安航天动力研究所,西安710100 [2]航天推进技术研究院,西安710025

出　　处：《导弹与航天运载技术（中英文）》2023年第2期31-35,共5页Missiles and Space Vehicles

摘　　要：发动机连续地面长程试车过程中,1根Ф11mm×1.5mm的液氧冷却导管断裂,断口位于焊缝热影响区,焊缝断口形貌显示为疲劳断裂。通过晶相分析、动力学仿真、疲劳试验和微观形貌分析,断裂主要原因为导管焊缝背面余高呈现较大散差、焊缝热影响区应力集中,导致寿命裕度降低、在发动机长时间工作条件下疲劳开裂。通过控制焊接余高和改为自动焊接工艺,可提高导管疲劳寿命。导管疲劳试验和地面试车验证了改进方法的有效性。A Pipe ofФ11mm×1.5mm specification for liquid oxygen cooling fractures during LOX/Kerosene engine ground hot-fire test.The fracture is located in the weld heat-affected zone.Through crystal phase analysis,dynamic simulation,fatigue test and microstructure analysis,the main reason of fracture is that the residual height on the back of the pipe weld shows a large divergence.The stress concentration in the heat affected zone of weld leads to the decrease of life margin.Fatigue crack occurs in engine long working conditions.The fatigue life of the pipe can be improved though control welding residual height and automatic welding process.The effectiveness of the improvement measures are verified in the fatigue life test and ground test.

关 键 词：液氧煤油发动机 导管 断裂 失效分析 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]