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为了深入了解固体火箭发动机高温高压环境中氧化铝沉积条件下绝热材料的传热烧蚀规律,从全尺寸发动机中液滴流动状态与沉积规律入手,结合凝聚相颗粒与壁面的相互作用机理,确定了Sommerfold数K作为壁面捕获准则,发展了一种能够模拟高温氧化铝沉积条件下绝热材料烧蚀的实验方法。三维两相数值模拟和实验结果表明:实验装置沉积段内凝相液滴流动状态与全尺寸发动机背壁凹腔内相似,且绝热材料烧蚀率相近。据此证明,此装置后续可用于开展氧化铝液滴沉积条件下绝热材料烧蚀特性的实验研究。
In order to understand deeply the heat transfer and ablation rule of the insulation material under the conditions of alumina deposition in the solid rocket motor under high temperature and high pressure, this paper starts with the flow pattern and deposition law of the droplets in the full-size engine, and determines the interaction mechanism between the particles and the wall surface The Sommerfold number K was used as a wall capture criterion to develop an experimental method that simulates the ablation of thermal insulation materials under high temperature alumina deposition. Three-dimensional two-phase numerical simulation and experimental results show that the flow state of the condensed-phase droplets in the sedimentation section of the experimental device is similar to that of the full-size engine back cavity, and the ablation rates of the thermal insulation materials are similar. This proves that this device can be used to carry out experimental research on the ablation characteristics of thermal insulation materials under the conditions of alumina droplet deposition.