Ablation properties of Mo/ZrC composite nozzle fabricated by plasma spray forming [等离子喷涂成型Mo/ZrC复合喷管的烧蚀性能研究]

作者：Wang Y.; Tang Q.; Yan Z.; Wang F.; Xiong X.

来源：Journal of Solid Rocket Technology, 2018, 41(6): 778-786.

DOI：10.7673/j.issn.1006-2793.2018.06.019

• Low pressure hot isostatic pressing
• Mo/ZrC composite nozzle
• Motor test
• Shrouded plasma spray forming
• Thermal shock and ablation behavior

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 HV 0.025 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.

• 出版日期2018
• 单位华南理工大学; 粉末冶金国家重点实验室; 中南大学