针对高性能航空发动机燃烧室进口马赫数不断提高,同时先进燃烧组织对流量分配及头部空气动力学的要求,设计出一种适用于可变几何燃烧室的新型燃烧室扩压装置—分配器式扩压器。通过试验研究,重点研究了分配器式扩压器的总压损失与马赫数以及面积比的关系,分配式扩压器挡板对流场的影响。结果表明:当马赫数为0.359时总压损失为3.57%,这说明扩压器总压损失符合要求；存在一个面积比1.6~2.1使得扩压器出口流畅分布均匀；挡板可以改变流场分布和入口压力参数。 

In consideration of inlet Mach number of the new generation aero-engine combustor rising continuously, and the demand of advanced combustor for airflow distribution and dome aerodynamics, a brand-new combustor distributor type diffuser was designed. Based on experiment,the total pressure loss throughout the diffuser changed along with mach number and area ratio was studied, and the impact on flow profile from the plates was obtained. The results show that the total pressure loss of distributor type diffuser is of 3.57% with Mach number 0.359, which means a proper loss throughout the diffuser.The flow uniformity in outlet of diffuser is good with the area ratio at 1.6~2.1,and the plate has an impact on flow and the inlet pressure. 