| 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 |
| DOI： |
| 分类号: |
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| Experimental Study on Vortex-Cooled Thrust Chamber |
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LI Jia-wen, TANG Fei, YU Nan-jia
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School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
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| 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 |
