等离子喷涂成型Mo/ZrC复合喷管的烧蚀性能研究  

Ablation properties of Mo/ZrC composite nozzle fabricated by plasma spray forming

作　　者：王跃明[1,2] 唐求豪 闫志巧 王芬[4] 熊翔[5] WANG Yueming;TANG Qiuhao;YAN Zhiqiao;WANG Fen;XIONG Xiang(Key Laboratory of High Efficiency & Precision Machining of Difficult-to-cut Material of Hunan Province, Hunan University of Science and Technology,Xiangtan 411201,China;Hunan Provincial Key Defense Laboratory of High Temperature Wear-Resisting Materials and Preparation Technology,Hunan University of Science and Technology, Xiangtan 411201,China;Guangdong Provincial Key Laboratory for Technology and Application of Metal Toughening, Guangdong Institute of Materials and Processing,Guangzhou 510650,China;National Engineering Research Center of Near-Net-Shape Forming for Metallic Materials,South China University of Technology,Guangzhou 510640,China;State Key Laboratory of Powder Metallurgy,Central South University,Changsha 410083,China)

机构地区：[1]湖南科技大学难加工材料高效精密加工湖南省重点实验室,湘潭411201 [2]湖南科技大学高温耐磨材料及制备技术湖南省国防科技重点实验室,湘潭411201 [3]广东省材料与加工研究所广东省金属强韧化技术与应用重点实验室,广州510650 [4]华南理工大学国家金属材料近净成形工程技术研究中心,广州510640 [5]中南大学粉末冶金国家重点实验室,长沙410083

出　　处：《固体火箭技术》2018年第6期778-786,共9页Journal of Solid Rocket Technology

基　　金：湖南省自然科学基金(2016JJ5029);湖南省军民融合产业发展专项资金资助项目(B116J1);材料成形与模具技术国家重点实验室(华中科技大学)开放基金(P2016-20);国家金属材料近净成形工程技术研究中心(华南理工大学)开放基金(2016003);广东省金属强韧化技术与应用重点实验室(广东省材料与加工研究所)开放基金(GKL201610)

摘　　要：采用化学包覆法制备Mo-(10%) ZrC复合喷涂粉末,采用气氛保护等离子喷涂成形技术结合低压热等静压致密化技术制备内径为8 mm、壁厚16.5 mm、长30 mm的某实验型固体火箭发动机Mo/ZrC复合喷管,测试喷管在地面点火试车条件下的抗热震烧蚀性能。研究结果表明,气氛保护等离子喷涂成形Mo/ZrC复合喷管经1800℃、10 MPa处理60 min后,微细ZrC颗粒均匀分布,断口晶粒仅2～5μm,致密度达94.5%。经1800℃、10 MPa处理300 min后,Mo/ZrC复合喷管由层片结构转化为颗粒状结构,致密度提高至96.8%,显微硬度及拉伸强度分别达259.8 HV0.025及138.9 MPa。地面试车实验后,Mo/ZrC复合喷管整体结构完好,未出现炸裂和破碎现象,抗热震烧蚀性能良好,其线烧蚀率仅为0.18 mm/20 s。地面试车过程中,机械剥蚀、熔化烧蚀及热化学烧蚀等三种烧蚀机制同时发生,Mo/ZrC复合喷管烧蚀程度依次为喉部>收敛段>扩散段。Molybdenum-10.0% zirconium carbide(Mo-10.0% ZrC) composite feedstock was fabricated by a chemical deposition method. Mo/ZrC composite nozzle(inner diameter of 8 mm,length of 30 mm and wall thickness of 16.5 mm) was produced by shrouded plasma spray forming(SPSF) followed by low pressure hot isostatic pressing(HIPing).The resistance of thermal shock and ablation property of Mo/ZrC composite nozzle was investigated by ablating test on a small solid rocket motor(SRM). After HIPing at 1800 ℃ and 10 MPa for 60 min,ZrC particles were evenly distributed in the deposits and molybdenum grains were fine(only 2 ~ 5 μm).Initial lamellar structure could be found in local regions of Mo/ZrC composite nozzle with relative to theoretical maximum density of about 94. 5%. After HIPing at 1800 ℃ and 10 MPa for 300 min,relative density of deposits with initial lamellar structure transforming into granular one was increased up to 96.8%.Micro-hardness and UTS of deposits were 259.8 HV0.025 and 138.9 MPa,respectively.After engine test,the specimen was integrated without cracks,which indicates that Mo/ZrC composite nozzle has good resistance to thermal shock and ablation.The line ablation rate of nozzle was only 0.18 mm/20 s. Three types of ablation mechanisms including mechanical erosion,thermophysical erosion,and thermochemical ablation took place during hot-firing test.The order of degree of ablation is as follows: nozzle throat>convergence>dilation inside Mo/ZrC composite nozzle.

关 键 词：Mo/ZrC复合喷管 气氛保护等离子喷涂 低压热等静压 发动机试车 抗热震烧蚀性能 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] TG146.412[一般工业技术—材料科学与工程]