论文部分内容阅读
为阐明液体冲压发动机的推力特性,对这种发动机的理论燃烧性能进行了研究,并与火箭冲压组合发动机进行了比较。在相同的燃料流量下,液体冲压发动机的比冲约为火箭冲压组合发动机的2倍。尤其使用JP-10等高密度燃料时,密度比冲也显示出优越性能。但研究发现,液体冲压发动机的燃烧效率和喷管流动效率受自大气中引入的空气流量影响较大。为取得较高的比冲,液体冲压发动机的空气流量远大于火箭冲压组合发动机的,进气口的性能对发动机性能的影响很大。为探讨液体冲压发动机的燃烧性能,试制了燃烧室内径为150mm的小型液体冲压发动机,进行了直连式燃烧试验。试制发动机在空燃比为50～140范围内稳定点火、燃烧,用C表征的燃烧效率达到90％以上。
In order to clarify the thrust characteristics of liquid ramjet engine, the theoretical combustion performance of this engine was studied and compared with rocket ramjet engine. At the same fuel flow rate, the hydraulic ramjet engine is about twice as compact as the rocket ramjet engine. In particular, the use of JP-10 and other high-density fuel density densification also showed superior performance. However, studies have found that the combustion efficiency of liquid ramjet engines and nozzle flow efficiency are greatly influenced by the air flow introduced from the atmosphere. In order to achieve a higher specific impulse, the air flow rate of the liquid ramjet engine is much larger than that of the rocket ramjet engine. The performance of the air inlet port greatly affects the engine performance. In order to discuss the combustion performance of liquid ramjet engine, a small liquid ramjet engine with a 150mm inner diameter of the combustion chamber was manufactured and the direct combustion test was carried out. The trial-manufacture engine stably ignited and burned in the air-fuel ratio range of 50-140, and the combustion efficiency as characterized by C reached more than 90%.