高温氧化铝液滴沉积条件下绝热材料烧蚀实验方法研究

Experimental Method Research on Ablation Characteristic of Insulation Material under High Temperature Alumina Droplet Deposition Condition

关键词:  固体火箭发动机  绝热层  沉积  烧蚀  实验装置

Key words:  Solid propellant rocket motor  Insulation material  Deposition  Ablation  Experimental device

摘要:

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。

Abstract:

In order to thoroughly understand the heat transfer and ablation law of insulation material in Solid Rocket Motor(SRM)under high temperature and high pressure environment，the liquid flow pattern and deposition law in full-scale rocket motor was discussed combined with the interaction mechanism between alumina droplet and solid surface. The Sommerfold number K was selected as the capture rule，then an experimental method was developed to simulate the ablation phenomenon of insulation material under high temperature alumina deposition. Three dimensional two phase numerical simulation and experimental results show that the alumina droplet flow state and insulation material ablation rate in lab-scale device are similar to chose of the back-wall cavity of the full-scale motor. Based on the above，it is proved that the lab-scale device can be used to perform the experimental study of the insulation material ablation characteristics under the condition of high temperature alumina droplet deposition in the future.