超燃冲压发动机燃烧室构型对燃烧室性能影响

Effects of scramjet combustor configuration on combustor performance

关键词:  超燃冲压发动机  燃烧室  构型  参数影响+  直连式试验+

Key words:  Scramjet  Combustor  Configuration  Parameter effect+  Direct-connect test+

摘要:

在超燃冲压发动机直连式试验台上,通过调节超燃冲压发动机燃烧室壁面扩张角和燃料喷注位置,对燃烧室构型进行了试验优化,并定量分析了燃烧室构型对燃烧室性能的影响。采用正交试验设计方法组织燃烧室形面调节,每个形面进行5种喷注位置的试验,每次试验通过文氏管调节燃料流量实现3个当量比的燃烧室工况。利用试验数据构造了燃烧室性能关于构型参数的响应面模型,经两次渐进优化获得了最佳燃烧室构型,其推力增益比基准构型增大了10.4%;试验误差小于5.0%,且试验调节参数基本呈正态分布;参数影响分析表明燃烧室性能受各耦合因素的强烈影响,各因素影响的差异不显著,且较小的第1级、第2级扩张角和较大的第3级、第4级燃烧室扩张角以及适当集中靠前喷油、适当提高当量比有利于获得更高的燃烧室性能。

Abstract:

An experimental study was conducted on the direct-connected scramjet combustor test system to investigate the optimization and effects of scramjet combustor configuration by adjusting the shape angles and fuel injection.An Orthogonal Array Design of Experiment(DOE) method was used to organize the combination of shape angles.For every combination,five experiments with different fuel injection arrangement were carried out,and every experiment was actualized with three equivalence ratios by adjusting a throttling venture.The test data were used to build the response surface model of the combustor performance with respect to configuration parameters,thus the optimal combustor configuration was obtained by twice successive optimization with thrust gain increased by 10.4% relative to that of the baseline configuration.The test error is less than 5.0%,and test parameters distribute almost with normal distribution.The effects of configuration parameters on combustor performance are analyzed quantitatively,and the result shows that the combustor performance is influenced strongly by the couple of configuration parameters.