带有辅助注气的喷管喉道面积控制方法研究  

Investigation of Axisymmetric Nozzle with Assisted Reinjection for Throat Area Control

作　　者：韩景[1] 额日其太[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空兵器》2011年第5期47-50,55,共5页Aero Weaponry

基　　金：航空科学基金资助项目(20080151007)

摘　　要：利用数值模拟方法,针对轴对称喷管,研究了主射流对辅助射流的影响,以及主射流流量、辅助注气缝宽度等参数对喷管流动和性能的影响规律。数值模拟结果表明,与普通喉道注气相比,喉道辅助注气可以在喉道下游产生更大的射流穿透深度和回流区,具有更好的喉道面积控制效果。随着主射流流量增大,喉道辅助注气流量逐渐增大,有效喉道面积逐渐减小。主射流流量较大时,可以形成开放的回流区,使喷管实际的膨胀比减小,提高喷管的推力性能。The flow fields of axisymmetric nozzles with assisted reinjection are simulated numerical- ly. The effects of injection flow and assisted reinjection slot width on nozzle flow and internal performance as well as the effect of throat injection flow on throat assisted reinjection flow are investigated. The results show that it gets larger recirculation regions in the downstream of throat and has better control effects for throat area using assisted reinjection than the usual throat injection nozzle. The throat assisted injection flow increases gradually, but the effective throat area decreases, along with the increase of injection flow. An open recirculation region can be formed when it has a larger injection flow, thus the actual expansion ratio of nozzle is decreased, and the thrust performance of nozzle is improved.

关 键 词：喷管 喉道面积控制 辅助注气 射流控制 

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]