线性可调音速喷嘴工作特性仿真  

Simulation on the performance of linear throttleable sonic nozzle

作　　者：成鹏[1] 李清廉[1] 张新桥[1] 康忠涛[1] 陈慧源[1] 

机构地区：[1]国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙410073

出　　处：《国防科技大学学报》2015年第6期48-53,共6页Journal of National University of Defense Technology

基　　金：新世纪优秀人才支持计划资助项目(NCET-13-0156)

摘　　要：为了满足组合发动机模态转换的要求,连续稳定调节推进剂流量十分关键。为此,针对气体推进剂,在常规音速喷嘴的基础上设计了一种可调音速喷嘴。通过塞锥改变音速喷嘴的节流面积,进而实现流量的连续调节。采用两次包络线方法设计塞锥型面,使得可调音速喷嘴具有线性的流量特性。采用计算流体动力学数值仿真研究可调音速喷嘴的工作特性。仿真结果表明反压小于临界反压时,可调音速喷嘴流量不受反压影响。可调音速喷嘴保持临界状态的临界反压比随流量的减小呈增大的趋势。线性可调音速喷嘴的流量与塞锥位置有较好的线性关系,其流量系数高且几乎不受塞锥位置的影响。The mode transition of combined-cycle engine makes it necessary to throttle the mass flow rate of propellants continuously and stably. Aiming at gaseous propellant, a throttleable sonic nozzle was designed on the basis of normal sonic nozzle. The throttleable sonic nozzle achieves continuous throttling through a plug moving along axis. By adopting the twice-envelope method, the contour of the plug was designed to satisfy the linear characteristic of mass flow rate. Performances of the throttleable sonic nozzle were investigated through the numerical simulation of computational fluid dynamics. It is found that the mass flow rate is independent under the back pressure when the back pressure is lower than the critical back pressure and the critical back pressure ratio increases as mass flow rate decreases. The linear relationship between mass flow rate of linear throttleable smlic nozzle and location of plug was verified and results show that the discharge coefficient is high and hardly be affected by the location of plug.

关 键 词：可调音速喷嘴 线性 流量特性 流量调节 反压 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]