Standing stability enhancement method of oblique detonation waves in a confined space and its experimental validation
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摘要: 采用斜爆震燃烧的高超声速冲压发动机是具有潜力的高马赫数吸气式推进技术方案。克服斜爆震的驻定稳定性问题对实现该技术方案至关重要。本文提出了一种封闭空间中的斜爆震驻定稳定性增强方法，并基于此方法开展了马赫数8.0近真实条件下的直连式试验验证。采用阵列喷管制造超声速预混气，通过关闭近壁单元中的燃料供应，在壁面附近制造了不可燃气体层，使斜爆震入射到壁面附近时衰减为惰性激波，从而削弱了斜爆震的马赫反射，防止了壅塞，增强了斜爆震的驻定稳定性，实现了近真实条件下长时间稳定驻定的斜爆震燃烧。Abstract: Hypersonic ramjets with the combustion mode of oblique detonation are promising in the high-Mach-number air-breathing propulsion field. It is very important to overcome the standing stability problem of oblique detonation waves for realizing this technical scheme. A standing stability enhancement method of oblique detonation waves in a confined space is proposed and validated in a direct-connect experiment under the Ma 8.0 near-real condition. Supersonic premixed gases are produced by using array nozzles and a non-reacting gas layer is formed by cutting off the fuel supply in the near-wall nozzle units. After the oblique detonation wave enters the near-wall region, it decays to an inert shock wave due to the presence of the non-reaction gas layer and therefore its Mach reflection on the wall can be significantly weakened to avoid choking flow. Through this method, the standing stability of oblique detonation waves is well enhanced and a long-time standing oblique detonation wave is obtained under the near-real condition.
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Key words:
- confined space /
- oblique detonation /
- standing stability /
- Mach reflection /
- direct-connect experiment
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图 1 斜爆震入射到尾喷管上沿示意图[21]
Figure 1. Schematic of oblique detonation wave incident on the upper edge of the exit nozzle
图 5 阵列喷管及其下游100 mm内的流场速度云图
Figure 5. Velocity magnitude contour inside the array nozzles and 100 mm downstream
图 6 y=206.4 mm上的马赫数和速度分布
Figure 6. Mach number and velocity magnitude distributions on the y=206.4 mm line
图 7 y=206.4 mm上的总温和总压分布
Figure 7. Total temperature and pressure distributions on the y=206.4 mm line
图 8 y=206.4 mm上的当量比分布
Figure 8. Equivalence ratio distributions on the y=206.4 mm line
图 10 不同流向位置的当量比分布
Figure 10. Equivalence ratio distributions at different streamwise locations
图 11 x=1500 mm处的速度、马赫数、温度和压力分布
Figure 11. Velocity, Mach number, temperature and pressure distributions at x=1500 mm
图 12 关闭壁面附近4个喷管单元的氢气后的流场在不同流向位置处的当量比分布
Figure 12. Equivalence ratio distributions at different streamwise locations when the hydrogen fuel of the four near-wall nozzle units are cut off
图 13 未采用和采用驻定稳定性增强方法的斜爆震流场对比
Figure 13. Comparison of oblique detonation flow fields without and with standing stability enhancement method
图 14 未采用驻定稳定性增强方法的斜爆震高速摄影照片
Figure 14. High-frequency camera photographs of the oblique detonation without standing stability enhancement method
图 15 采用驻定稳定性增强方法的斜爆震高速摄影照片
Figure 15. High-frequency camera photographs of the oblique detonation with standing stability enhancement method
图 16 采用驻定稳定性增强方法的燃烧室尾焰照片
Figure 16. Exit flame of the combustor with standing stability enhancement method
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