旋流对轴对称喷管性能影响的数值研究  

Numerical study of the swirl flow effects on the performance of axisymmetric nozzle

作　　者：刘巍[1] 杨涛[1] 程兴华[1] 李理[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《航空动力学报》2010年第3期709-712,共4页Journal of Aerospace Power

基　　金：国家自然科学基金(50376072)

摘　　要：为了研究旋流进气对喷管性能参数的影响,使用数值模拟的方法对轴对称喷管直流进气与旋流进气两种工作状态进行了对比研究,分析了不同空气流量、不同旋流强度下的喷管流量系数、真空推力系数以及比冲的变化规律.研究发现,使用喷管入口轴向质量平均总压计算所得喷管性能参数不随旋流强度的变化而变化,且与直流状态近似相等;旋流的切向动压随旋流数的增大而增大,但对喷管推力没有贡献,应将其归入总压损失.In order to study the swirl flow effects on the performance of axisymmetric nozzle, the flow field in axisymmetric nozzle was numerically simulated under both swirl flow and straight flow conditions. The flow coefficient, vacuum thrust coefficient and specific impulse of the nozzle were studied with different air mass flow rates and swirl intensities. It is concluded that the flow coefficient, vacuum thrust coefficient and specific impulse are not changed under different swirl intensities if calculated from the axial mass average total pressure at the nozzle inlet. The tangential dynamic pressure increase at the nozzle inlet with the swirl number enlarged at the combustion chamber inlet, and do not contribute to the thrust, so it should be looked as another type of total pressure loss.

关 键 词：旋流 喷管 流量系数 真空推力系数 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]