摘要
以3.0%火焰筒压力损失火焰筒作为基准,分别设计了2.5%和2.0%火焰筒压力损失的火焰筒,通过试验研究火焰筒压力损失对地面起动点火性能的影响,对火焰筒内部流场进行数值模拟.在火焰筒压力降3.0%以内的空气条件下,3种方案贫油点火边界基本一致,低压力损失火焰筒能够在更宽的压力降条件下点燃,2.5%方案的综合点火性能最好.结合数值模拟结果:压力损失降低至2.0%,流场结构与基准方案有较大的区别,对燃烧室的性能开始产生不利影响,2.5%方案与基准方案流场结构较为接近,定量的变化对燃烧室的性能影响是有益的.
Based on a combustor of 3.0% liner pressure loss,two low pressure loss liners（2.5% and 2.0%） were designed.The light lean ignition experiments and numerical simulation were conducted to study the effect of liner pressure loss on the combustor ignition performance.On the condition of pressure drop less than 3%,the ignition performances were almost the same.On the condition of pressure drop greater than 3%,the ignition performances of low liner pressure loss were better than that of the baseline liner,and 2.5% pressure loss liner was the best of the overall ignition performance.Combined with numerical simulation results,the flow structure of liner of 2.0% pressure loss was significantly different from that of the baseline liner,which had a negative effect on the performance of ignition.The flow structure of liner of 2.5% pressure loss was similar with that of the baseline liner,which had a positive effect on the performance of ignition.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第10期2229-2235,共7页
Journal of Aerospace Power
