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在某直径6cm级的微型涡轮发动机MJ-S1研制中微型扩压器方案得到了改进,改进型微型扩压器由完整的主叶片和通道后部的分流叶片构成,可以避免气流的强烈掺混,降低转弯段内气流速度,减小流动损失.介绍了这种扩压器的设计方法,采用数值模拟的方法研究了设计参数通道面积和叶片角分布对扩压器性能的影响.MJ-S1最佳的改进型扩压器具有上凸的通道面积分布和接近线性的叶片角分布,该扩压器在压气机级中工作时总压恢复系数接近0.9.
In a 6cm diameter micro-turbine engine MJ-S1 developed micro-diffuser scheme has been improved, improved micro-diffuser from the main blade and the back of the channel splitter blade composition, to avoid the strong mixing airflow , To reduce the airflow velocity in the turning section and reduce the flow loss.The design method of this diffuser is introduced and the influence of the design parameters of the passage area and the angular distribution of the blade on the performance of the diffuser is studied by numerical simulation.MJ-S1 The best improved diffuser has a convex channel area distribution and a near-linear blade angle distribution. The diffuser has a total pressure recovery coefficient of approximately 0.9 when operating in the compressor stage.