火箭推进2018，Vol.44Issue(6)：14-20,7.
组合循环发动机轴对称环形可调喷管方案研究
Study on adjustable axisymmetric annular nozzle of combined cycle propulsion system
摘要
Abstract
One new scheme about adjustable axisymmetric annular nozzle for dual flow path of CCP (combined cycle propulsion) system is presented in this study. The numerical simulation of nozzle's 3 D flow field at specific operating conditions was carried out, and a comparison with fixed nozzle and nozzle without diverging part was done. The results show that the continuous adjustment of throat area and expansion ratio of the area can be achieved by driving the external cowl to move along the axial direction, which can improve the thrust performance of the nozzle effectively. The thrust coefficients of the adjustable nozzles are above 0. 93 and even reaches 0. 974 under the typical conditions of Ma 2 ～ 5. The fixed nozzle can't satisfied the need of engine at the off-design point, but mass flow rate of the adjustable nozzle can match the mass flow rate upstream of engine precisely due to its adjustable throat area. The maximum deviation of mass flow rate between the fixed nozzle and adjustable nozzle can reach 50. 6％.The thrust coefficient of adjustable annular nozzle is higher than that of the fixed nozzle and the nozzle without diverging part. Under the same flight condition, the thrust coefficient of adjustable nozzle is 31％higher than the fixed nozzle, and 14. 6％ higher than the nozzle without diverging part.关键词
组合循环发动机/双流道/环形可调喷管/仿真分析Key words
CCP system/dual flow path/adjustable annular nozzle/simulation analysis分类
航空航天引用本文复制引用
张留欢,王君,马元,南向谊,张蒙正..组合循环发动机轴对称环形可调喷管方案研究[J].火箭推进,2018,44(6):14-20,7.基金项目
装备预研航天科技联合基金(6141B0606260401) （6141B0606260401）
