局部热-力耦合环境调控下C/C-HfC-SiC复合材料的氧化层演化与烧蚀行为

doi:10.15541/jim20260110

摘要/Abstract

摘要： C/C-HfC-SiC复合材料是高速飞行器热防护系统的关键候选材料。在极端服役条件下,结构表面同时承受高温热流与高速气流冲刷,形成复杂的局部热-力耦合环境,从而显著影响表面氧化层的形成与稳定性。为揭示局部烧蚀环境对表面氧化层动态行为及失效机理的调控规律,本研究设计并制备了环形试样以模拟发动机喉衬结构,采用氧-乙炔火焰进行烧蚀实验,在距离喷嘴10 mm (D10试样)和15 mm (D15试样)的喷距下构建两种典型的热-力耦合环境,分别对应高热流/高气流剪切作用与较低热流/较低气流剪切作用环境,并系统研究了其对环形试样不同特征表面氧化层行为及抗烧蚀性能的影响。结果表明,氧化层在不同表面区域差异明显。在驻点区(α面),氧化层行为主要受温度控制：D10试样在较高温度下形成致密的HfO₂-SiO₂复合氧化层并表现出主动修复能力,而D15试样因温度较低,氧化层生成速率不足,在氧化层局部受损或剥落后难以及时生成并覆盖表面。在平行流区(β面),氧化层形貌则主要由气流剪切作用调控：高气流剪切作用环境(D10试样)下HfO₂被拖曳铺展形成连续薄膜,而低气流剪切环境 (D15) 中气态副产物聚集形成离散球壳结构,该结构易破碎且防护能力有限。上述差异最终反映在整体烧蚀行为上,五轮循环烧蚀 (600 s) 后D10与D15试样的平均质量烧蚀率分别为0.038和0.067 mg/s。研究表明,氧化层生成主要由温度驱动,而其迁移与形貌演化则受气流剪切作用调控。

关键词: C/C复合材料, 基体改性, 反应熔渗, 前驱体浸渍裂解, 烧蚀

Abstract: C/C-HfC-SiC composites are considered promising candidate materials for thermal protection systems in hypersonic vehicles. Under extreme service conditions, structural surfaces are simultaneously exposed to intense aerodynamic heating and high-velocity gas flow, creating complex localized thermo-mechanical environments that strongly influence the formation and stability of protective oxide layers. To clarify how local ablation environments regulate the dynamic evolution and failure behavior of surface oxide layers, annular specimens were designed and fabricated to simulate the throat-liner structure of propulsion systems. Oxy-acetylene torch tests were performed at stand-off distances of 10 mm (Sample D10) and 15 mm (Sample D15), creating two representative thermo-mechanical environments characterized by high heat flux/high aerodynamic shear and relatively lower heat flux/lower aerodynamic shear , respectively. The resulting effects on the oxide-layer evolution and ablation resistance across different characteristic surfaces of the annular specimens were systematically investigated. Distinct oxide-layer behaviors were observed in different surface regions. In the stagnation region (α surface), oxide evolution is primarily governed by temperature. Under the higher temperature condition at D10, a dense HfO₂-SiO₂ composite oxide layer forms and exhibits pronounced self-healing capability. In contrast, the lower temperature at D15leads to a slower oxide formation rate, making it difficult for the oxide layer to form promptly and re-cover the surface after local damage or spallation. . In the parallel-flow region (β surface), the oxide morphology is mainly governed by aerodynamic shear. Under high aerodynamic shear (D10), HfO₂ is dragged and spread into a continuous thin film. Under lower aerodynamic shear (D15) gaseous by-products accumulate to form discrete spherical-shell structures, which are mechanically fragile and thus less protective. These differences are ultimately reflected in the overall ablation performance. After five ablation cycles (600 s), the average mass ablation rates of D10 and D15 are 0.038 and 0.067 mg/s, respectively. The results reveal that oxide formation is primarily driven by temperature, whereas oxide migration and morphological evolution are regulated by aerodynamic shear.

Key words: C/C-HfC-SiC composite, matrix modification, reactive melt infiltration, polymer impregnation and pyrolysis, ablation

中图分类号:

TB332

常梦圆, 李克智, 张佳平, 王润宁. 局部热-力耦合环境调控下C/C-HfC-SiC复合材料的氧化层演化与烧蚀行为[J]. 无机材料学报, DOI: 10.15541/jim20260110.

CHANG Mengyuan, LI Kezhi, ZHANG Jiaping, WANG Running. Oxide-layer Evolution and Ablation Behavior of C/C-HfC-SiC Composites under Localized Thermo-mechanical Coupling[J]. Journal of Inorganic Materials, DOI: 10.15541/jim20260110.

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