扩张段注气对扩张型双喉道喷管起动的影响研究  

Effect of Injection at Divergent Section on Starting Problem of Divergent Dual Throat Nozzle

作　　者：王健[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：《航空工程进展》2011年第3期318-322,329,共6页Advances in Aeronautical Science and Engineering

基　　金：航空科学基金(20080151007)

摘　　要：扩张型双喉道喷管存在起动问题,使喷管推力性能显著下降。为此,提出了扩张段注气解决喷管起动问题的方案,并利用数值模拟方法,针对二元扩张型双喉道喷管,研究了扩张段注气压比、注气位置等对喷管流动和性能的影响。研究结果表明:扩张段注气可以产生斜激波系和大的分离区,改变了扩张型双喉道喷管主气流通道的形状,减小了激波损失,解决了喷管的起动问题,并使喷管性能显著提高;注气缝位于扩张段中间时,容易形成连续扩张的主流通道,有利于主流的加速和产生推力,因此其推力性能最好。A scheme of injection at the divergent section is put forward to solve the starting problem in the divergent dual throat nozzle.The effects of the injection flow at the divergent section and the injection location on the flow and the performance of the nozzle are studied by two-dimensional divergent numerical simulation.Results indicate that oblique shock series and large separation areas can be made by the injection at the divergent section and change the flow channel shape of the divergent dual throat nozzle,so that the shock losses are reduced,the nozzle starting problem is solved,and the dual throat nozzle performance is remarkably improved.When the injection slot is in the middle of the divergent section,the continuous divergent channel is easily formed,it is helpful to accelerate the main stream and to generate the thrust,and the best thrust performance can be obtained on this condition.

关 键 词：矢量喷管 双喉道喷管 扩张段注气 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]