Abstract: The vortex-cooled thrust chamber is an alternative cooling approach that can potentially offer additional benefits and design flexibility for liquid propellant thrust chambers. Based on the theoretical analysis and numerical simulation, a vortex-cooled thrust chamber for experiment using GH₂/GO₂ was designed.Cold flow and hot-fire tests were conducted. Without using other cooling methods, a 20-second hot-fire test was accomplished. The results of the investigation indicate that the vortex-cooled thrust chamber operates in steady-state and the GO₂ forms the effective cooling vortex. The temperature increase of exterior surface of the chamber wall is 5K. In addition, the nozzle is protected effectively by cold gas film introduced by a portion of GO₂.

Key words: Liquid rocket engine; Vortex-cooled thrust chamber; Hot-fire test

摘要： 涡流冷却是一种新型液体火箭发动机推力室冷却技术。在理论分析和数值计算的基础上,设计了采用气氢/气氧作为推进剂的试验用涡流冷却推力室,进行了多次冷流试验和点火试验。在不采用其它冷却措施的情况下,完成了工作时间为20s的点火试验。试验结果表明,涡流冷却推力室工作稳定,气氧形成了有效的冷涡流,圆筒段外壁面温升为5K,部分气氧形成的气膜也对喷管形成了有效的保护。

关键词: 液体火箭发动机;涡流冷却推力室;点火试验