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本文简要地叙述了小推力、长时间工作的固体火箭发动机长喷管的烧蚀、冲刷和隔热问题的试验研究工作。对研制过程中所遇到的不同材料在高温下的热膨胀及喷管穿火和喉部烧蚀、冲刷等问题进行了探讨。着重指出:对烧蚀、隔热采用的不同材料在结构上必须考虑高温下的热膨胀补偿及气体挥发份的逸出;整体钨渗铜喉衬入口处形成的“烧蚀台阶”造成该处流场的严重扰动,是导致喷管穿火的重要因素。另外,对造成钨渗铜喉部烧蚀、冲刷的各种因素进行了分析,认为含有大量固体微粒(A1_2O_3)的高温高压高速燃气流对喉部壁的机械冲刷是主要原因。为此,正确选择整体钨渗铜喉衬内型面结构参数以减小燃气流对喉部的机械冲刷作用是解决喉部烧蚀、冲刷的关键。 试验结果表明,采取相应的改进措施后,目前的长喷管设计是成功的。
This paper briefly describes the experimental research on the ablation, erosion and heat insulation of long nozzle of solid rocket engine with small thrust and long working time. The thermal expansion of different materials encountered in the process of development, as well as the penetration through the nozzle and the laryngeal ablation and scouring were discussed. It is emphatically pointed out that different materials used for ablation and insulation must be structurally compensated for the thermal expansion at high temperatures and escaping gas volatiles; the “ablation step” formed at the entrance of the overall tungsten-infiltrated copper throat lining causes this flow Serious disturbance of the field is an important factor that leads to the fire through the nozzle. In addition, various factors that cause the ablation and erosion of tungsten-copper-coated throat are analyzed. It is considered that the high-temperature and high-pressure gas stream containing a large amount of solid particles (A1_2O_3) is the main reason for the mechanical erosion of the throat wall. For this reason, the key to solve the laryngeal ablation and erosion is to correctly select the structural parameters of the overall tungsten infiltration copper liner inner profile to reduce the mechanical scouring effect of the gas flow on the larynx. The test results show that the current long nozzle design is successful after corresponding improvement measures are taken.