火箭推进

提出一种基于旋转爆震的涡轮基组合循环发动机系统方案,整体采用并联式布局,可根据飞行器的工作条件在3种模式之间转换,从而满足全速域、跨空间高超声速飞行器的动力需求。针对涡轮单元和冲压单元的性能特征,提出一种等推力等流量模态转换策略,进一步揭示了模态转换规律及过渡模态总体性能特征。结果表明:旋转爆震技术的应用能够显著改善燃气涡轮发动机的高速性能以及冲压发动机的低速性能; 模式转换起始马赫数越高,过渡模式比推力越小,比冲越高。

An over-under configuration of the rotating detonative airbreathing combined cycle engine is presented in this study. Two propulsion units are merged to achieve three different operating modes,which provides a favorable propulsion choice for advanced full range and trans-aerosphere hypersonic vehicles. Based on the steady state characteristics of turbine and ramjet units,a mode transition strategy with equal thrust and equal mass flowrate is proposed for the combined cycle engine,which further reveals the mode transition strategy and overall performance of the transition mode. The results indicate that the rotating detonation ramjet engine shows potential for improving the overall performance in low flight Mach number regime,and the rotating detonation turbojet engine shows potential for improving the overall performance in high flight Mach number regime. The higher the initial Mach number of mode transition,the lower the specific thrust and the higher the specific impulse during the transition mode.

引言
1 数学物理模型
2 结果与讨论
3 结论

图1 旋转爆震燃烧室典型流场示意图<br/>Fig.1 Schematic diagram of typical flow field in rotating detonation combustor

图1 旋转爆震燃烧室典型流场示意图
Fig.1 Schematic diagram of typical flow field in rotating detonation combustor

图2 旋转爆震燃烧室低阶模型计算结果与数值模拟结果的比较<br/>Fig.2 Comparison of low-order model calculation results with numerical simulation results for rotating detonation combustor

图2 旋转爆震燃烧室低阶模型计算结果与数值模拟结果的比较
Fig.2 Comparison of low-order model calculation results with numerical simulation results for rotating detonation combustor

图3 基于旋转爆震的涡轮基组合循环发动机系统方案<br/>Fig.3 Turbine-based combined cycle engine based on rotating detonation

图3 基于旋转爆震的涡轮基组合循环发动机系统方案
Fig.3 Turbine-based combined cycle engine based on rotating detonation

图4 组合循环发动机的工作模式<br/>Fig.4 Operating mode of combined cycle engine

图4 组合循环发动机的工作模式
Fig.4 Operating mode of combined cycle engine

图5 旋转爆震涡轮发动机与常规涡轮发动机的性能比较<br/>Fig.5 Performance comparison between rotating detonation turbine engine and traditional turbine engine

图5 旋转爆震涡轮发动机与常规涡轮发动机的性能比较
Fig.5 Performance comparison between rotating detonation turbine engine and traditional turbine engine

图6 旋转爆震冲压发动机与常规冲压发动机的性能比较<br/>Fig.6 Performance comparison between rotating detonation ramjet engine and traditional ramjet engine

图6 旋转爆震冲压发动机与常规冲压发动机的性能比较
Fig.6 Performance comparison between rotating detonation ramjet engine and traditional ramjet engine

图7 定高巡航工况下H取值对组合循环发动机总体性能和进气道流量分配的影响<br/>Fig.7 Influence of H value on the overall performance of combined cycle engine and the inlet flow distribution under the constant height cruise condition

图7 定高巡航工况下H取值对组合循环发动机总体性能和进气道流量分配的影响
Fig.7 Influence of H value on the overall performance of combined cycle engine and the inlet flow distribution under the constant height cruise condition

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备注

引言

1 数学物理模型

2 结果与讨论

3 结论

期刊信息