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超燃冲压发动机燃烧室主动冷却模型制造和热考核试验的费用高昂、周期长,为了降低试验风险,采用三维计算和经济的验证试验相结合的方法开展了超燃冲压发动机燃烧室主动冷却设计。冷却结构基本参数设计和侧壁冷却流动设计是确定设计方案的两大基础,前者采用三维传热计算结合冷却面板传热验证试验完成,后者采用超临界燃料流动三维并行计算结合水流动验证试验完成。在此基础上,经过多轮的结构设计与三维传热及强度计算评估迭代,确定了最终的燃烧室主动冷却结构。设计的主动冷却燃烧室在来流马赫数2.5,总温1700K条件下成功通过200s热考核试验,表明所采用的设计方法、验证试验和计算工具是有效和可信的。
In order to reduce the risk of test, the active cooling model manufacturing and thermal test of scramjet engine combustion chamber are costly and long cycle. In order to reduce the test risk, the active cooling design of the combustion chamber of scramjet engine was carried out by a combination of three-dimensional calculation and economic verification test. The basic parameters of the cooling structure and the design of the cooling flow in the side wall are two major bases for determining the design scheme. The former is accomplished by the three-dimensional heat transfer calculation combined with the heat transfer verification of the cooling panel. The latter uses the three-dimensional parallel calculation of the supercritical fuel flow combined with the water flow verification test carry out. On this basis, after many rounds of structural design and three-dimensional heat transfer and strength calculation and evaluation iteration, the final combustion chamber active cooling structure is determined. The designed active cooling combustor successfully passed the 200s thermal test at a Mach 2.5 flow rate and a total temperature of 1700K, indicating that the design methodology used, the verification test, and the calculation tools are valid and credible.