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复杂力热载荷下推力室内壁失效机理研究

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大推力氢氧火箭发动机在经过多次试车后,推力室内壁会产生不同程度的裂纹,严重影响发动机的工作可靠性.为了分析复杂力热载荷下推力室内壁的失效机理,本文根据发动机实际工作过程涉及预冷-工作-后冷-松弛四个阶段,分别计算了经过单次和多次工作循环的内壁应力应变情况,并针对试车分解后的内壁材料进行断貌分析和金相检查.仿真与材料分析结果表明:内壁面的失效机理为疲劳和棘轮共同作用下导致通道中心点处残余拉应变不断累积,不断向外鼓起,而内壁材料在高温下会出现晶粒粗化和再结晶现象,导致材料性能出现不可逆的下降,加速了结构失效,最终产生裂纹.
Study on Failure Mechanism of Thrust Chamber Liner Wall under Complex Thermal Load
The liner wall of high-thrust hydrogen-oxygen rocket engine will crack in different degree after several tests,which will seriously affect the working reliability of the engine.In order to analyze the failure mechanism of thrust chamber wall under complex thermal load,according to the four stages of precooling-working-postcooling-relaxation involved in the actual working process,the stress and strain of the inner wall after single and multiple working cycles are calculated respectively,and the crack failure analysis and metallographic analysis are carried out for the inner wall material after decomposing.The results of simulation and material analysis show that the failure mechanism of the inner wall is that the residual tensile strain accumulates at the central point of the channel under the action of fatigue and ratchet,and the grain coarsening and recrystallization occur in the inner wall material at high temperature,which leads to the irreversible decline of the material properties,accelerates the failure of the structure and eventually produces cracks.

thrust chamberfailure mechanismfatiguefracture analysiscrack

吴有亮、刘潇、孙冰、金平、田原

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北京航天动力研究所 低温液体推进技术实验室,北京 100076

北京航空航天大学 宇航学院,北京 100191

推力室 失效机理 疲劳 断貌分析 裂纹

民用航天科研工程项目

D010103

2024

强度与环境
北京强度环境研究所

强度与环境

CSTPCD
影响因子:0.45
ISSN:1006-3919
年,卷(期):2024.51(1)
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