Flow Mechanism of Oblique Detonation Engines
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摘要: 为了研究高Mach数超燃冲压发动机和斜爆轰发动机的内流场燃烧流动机理，首先用CJ爆轰理论对超燃冲压发动机的内流场特性进行了理论分析，给出了燃烧室流场的气动规律，理论分析结果与现有实验结果吻合得非常好.其次，根据理论分析结果，提出了高Mach数超燃冲压发动机和斜爆轰发动机的气动设计原则.最后，根据提出的气动设计原则，设计了高Mach数斜爆轰发动机，飞行Mach数为9，对斜激波诱导燃烧机理开展了二维数值模拟研究.数值模拟结果表明，在高Mach数下，斜爆轰发动机燃烧室内可以得到稳定的燃烧流场.Abstract: The theoretical analysis of the aerodynamic characteristics of high Mach number air-breathing engines is very important for the design and optimization of scramjet or oblique detonation engines. However, due to the varying incoming flow conditions and the complexity of the flow dynamics inside the engines, establishing a satisfactory theoretical model is very difficult. In this paper, firstly, the aerodynamic characteristics of scramjet engines were theoretically analyzed by using CJ detonation theory and some general regulations were obtained. The analysis results are in good agreement with the experimental results. Then, the aerodynamic design principles for oblique detonation engines were put forward based on these theoretical analysis results. Finally, an oblique detonation engine was designed according to these aerodynamic design principles. Two-dimensional numerical simulations were conducted to simulate its combustion flow field. The numerical results demonstrate that steady combustion flow field can be obtained in oblique detonation engines at high flight Mach numbers.
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Key words:
- oblique detonation engine /
- scramjet /
- supersonic combustion /
- detonation /
- shock induced combustion
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图 6 Hyshot Ⅱ数值模拟结果与实验结果比较
Figure 6. Comparisons of CFD results of HyShot Ⅱ with DLR experimental results
图 7 斜爆轰发动机的压力云图和OH质量分数云图
Figure 7. Contours of pressure and mass fraction of OH with Φ=1.0
图 9 燃烧室内的温度云图和H2O质量分数等值线:实线为流线; 虚线为H2O质量分数
Figure 9. Temperature contours in the combustor and mass fraction of H2O :numbers and isolines
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