Influence of liquid fuel on the detonation characteristics of continuous rotating detonation engine
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摘要: 为了研究液态燃料对连续旋转爆轰发动机爆轰特性的影响，采用CE/SE方法对以汽油/富氧空气为燃料的CRDE进行数值模拟，分析了不同液滴半径、当量比对爆轰性能参数的影响。计算结果表明：随着液滴半径增大，爆轰压力峰值、温度峰值以及爆轰波速度均降低，且压力峰值与温度峰值在爆轰波传播过程中出现不稳定现象；当增大到70 μm时，爆轰波将无法成功起爆。随着当量比的增大，CRDE爆轰波速度及平均推力增大，爆轰压力、温度以及气相周向速度的峰值均先增大后减小。在当量比1.1附近，爆轰压力与温度的峰值出现极大值；而气相周向速度峰值的极大值出现在当量比0.9附近。基于燃料的比冲随着当量比增大而减小。Abstract: In this paper, based on two-dimensional conservation element and solution element(CE/SE), we simulated the detonation process of CRDE with gasoline and oxygen-enriched air to study the influence of liquid fuel on the detonation characteristics of the continuous rotating detonation engine. The effects of different droplet radiuses and equivalence ratios on the detonation parameters were analyzed. Our calculation results show that the velocity of the detonation wave and the peak values of the detonation pressure and temperature decreased with the increase of the droplet radius, and the peak values of the pressure and temperature became unstable during the propagation of the detonation wave. However, the detonation wave were not initiated successfully when the radius rose to 70 μm. The velocity of the detonation wave and the average thrust of CRDE increased with the rising of the equivalence ratio, while the peak values of the detonation pressure, temperature and gas phase's circumferential velocity increased first and then decreased. The peak values of the detonation pressure and temperature reached the maximum when the equivalence ratio was about 1.1, while the maximum of the gas phase's circumferential velocity occurred when the equivalence ratio was about 0.9.The fuel-based specific impulse decreased at the increase of the equivalence ratio.
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Key words:
- filling conditions /
- continuous rotating detonation engine /
- CE/SE /
- specific impulse
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图 3 燃烧室内流场分布情况(t=1 276 μs)
Figure 3. Distribution of flow field in combustor (t=1 276 μs)
图 4 燃烧室入口处流场分布(t=1 276 μs)
Figure 4. Distribution of flow field of combustor inlet (t=1 276 μs)
图 6 压力和温度随时间变化曲线(x=0.2 m, y=0 m)
Figure 6. Variation curves of pressure and temperature with time (x=0.2 m, y=0 m)
图 8 不同当量比条件下的平均推力和基于燃料的比冲变化情况
Figure 8. Variation curves of average thrust and specific impulse
图 7 爆轰参数随当量比变化曲线
Figure 7. Variation curve of detonation parameters with equivalence ratio
表 1 不同液滴半径条件下爆轰情况
Table 1. Parameters of detonation at different droplet radius
液滴半径/μm 爆轰压力峰值/MPa 爆轰温度峰值/K 爆轰波速度/(m·s-1) 20 4.20 3 050 1 568 30 4.11 2 957 1 466 40 3.65 2 743 1 370 50 3.35 2 608 1 265 60 2.78 2 553 1 165 70 - - - 
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