Scramjet combustor design optimization for a test scramjet model engine is conducted by employing genetic algorithms, and an optimal design much better than original design is obtained.
采用遗传算法对某试验超燃冲压模型发动机的燃烧室构型参数进行了优化设计，所得方案的性能大大优于实际方案。
The preliminary test result shows that the combustor can be reliably ignited under the condition of large nozzle throat, the combustion process is stable and combustion efficiency is high.
初步研究结果表明，该方案在大喷管条件下点火起动可靠，燃烧过程比较稳定，燃烧效率高。
To cope with such problems, the author recommends an improved design for the combustor local cooling with measuring and test data being given in the paper.
为解除故障，对火焰筒进行了局部冷却结构的改进设计。文中并给出了测试数据。
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