摘要
针对高性能航空发动机燃烧室进口马赫数不断提高,以及先进变几何燃烧室燃烧组织特点,设计出一种新型可变几何燃烧室扩压装置—分配器式扩压器。通过试验研究了面积比、马赫数与总压损失的关系。结果表明:冷却模和燃烧模的总压损失与其开孔面积,以及孔形有关。各个模之间的影响与面积百分比有关;卷边孔挡板可以有效减少总压损失。
In consideration of inlet mach number of the new generation aero-engine combustor rising continuously and the demand of advanced variable-geometry combustor,a brand-new combustor distributor type diffuser was designed.Based on experiment,the total pressure loss of distributor type diffuser vs mach number and area ratio was studied.The results show that the total pressure loss in dome cooling module was related with the area and the scheme of holes.The interaction between cooling module and combustion module dependes on the area fraction.The edge folded holes in the plates can decrease obviously the total pressure loss.
出处
《科学技术与工程》
北大核心
2012年第11期2631-2636,共6页
Science Technology and Engineering
