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本报告描述了两种液体燃料冲压发动机燃烧室——4管进气和2管进气的侧边突扩燃烧室的试验研究:给出了这两种燃烧室的稳定性数据、燃烧效率数据和压力振荡数据。此外,为了比较,文中还包括了以前报告中提供的固体管道火箭燃烧室的数据。燃烧室台架试验表明,2管进气燃烧室的压力振荡比4管进气燃烧室高得多。在燃烧室水模试验研究中,得到了相应的结果(不稳定流型)。尤其是,在2管进气燃烧室中发现了一个脉动涡系。水模试验还指出了如何修改燃油喷射系统,才能避免燃油喷入这一涡系,据此进行的燃烧室台架试验证实了压力振荡显著衰减。
This report describes the experimental study of two liquid-fuel stamped engine combustors - a 4-cylinder inlet and a 2-inlet side flared combustion chamber: gives the stability data for both chambers, the combustion efficiency data And pressure oscillation data. In addition, for comparison purposes, the data included in the previous report for the solid pipeline rocket combustion chamber was also included. Combustion chamber bench tests show that the pressure oscillations in the 2-inlet gas combustion chamber are much higher than those in the 4-inlet gas combustion chamber. Corresponding results (unstable flow pattern) were obtained in the experimental study of the combustion chamber model. In particular, a pulsating vortex was found in the 2-inlet combustion chamber. The water model test also pointed out how to modify the fuel injection system to avoid fuel injection into the vortex system. The combustion chamber bench test thus verified shows that the pressure oscillation is significantly attenuated.