THE LAW OF TOTAL PRESSURE OF OBLIQUE DETONATION WAVE AND ITS APPLICATION IN DETONATION ENGINE ANALYSIS MODEL
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摘要: 爆轰推进系统具有热循环效率高和燃烧速率快等优点, 逐渐展露出将取代传统动力技术的趋势, 在高超声速飞行器推进领域中具有广阔应用前景. 对推进系统而言, 气流总压损失需要尽可能小, 从全解域出发研究斜爆轰波总压特性有利于在爆轰推进系统的概念设计阶段控制总压损失量值. 文章关注于已经形成稳定的斜爆轰波面, 将斜爆轰波视为有瞬时能量添加的斜激波, 利用极曲线方法研究斜爆轰波总压损失问题. 以波前法向马赫数作为爆轰波强度表征量, 推导出斜爆轰波强度关系式, 发现绝热斜激波强度最弱关系式同样适用于斜爆轰波. 借用激波图解法, 证明了斜爆轰波最小总压损失特性仍然存在, 并进一步揭示了最小总压损失线会随着添加能量的增大而向更大的爆轰角偏移, 而原本对称的总压损失规律被打破. 此外, 还获得了增加能量大小和诱导爆轰楔面角度对最小总压损失的影响规律, 发现当获得的能量越多而楔面角度越小时斜爆轰波总压损失极值点越容易向更大的爆轰角偏移. 最后, 根据斜爆轰波总压特性, 提出了一种可提高发动机总压理论上限的简化设计思路, 斜爆轰波总压规律可为斜爆轰发动机的概念设计提供参考.Abstract: Detonation propulsion system has the advantages of high thermodynamic efficiency and fast heat release, which gradually shows the trend of replacing traditional propulsive technology, and has broad application prospects in hypersonic air-breathing propulsion systems. For the propulsion system, the total pressure loss should be as small as possible. Studying the total pressure characteristics from the global solution domain of oblique detonation wave is beneficial to control the total pressure loss level in the conceptual design stage of the detonation propulsion system. In this paper, the formed and stable oblique detonation waves are focused, and simplified into a discontinuity with energy input. The total pressure loss of oblique detonation wave is studied by using the shock polar. Taking the normal Mach number before oblique detonation wave to represent the strength of oblique detonation, the relations of oblique detonation wave are derived. It is found that the law of the weakest shock wave strength of oblique shock is also applicable to oblique detonation wave. By using shock efficiency diagram, it is proved that the minimum total pressure loss characteristic of oblique detonation still exists, and it is further revealed that the minimum total pressure loss line will shift to a larger shock angle with energy input, and the symmetrical relation of total pressure loss is broken. In addition, the effects of the amount of input energy by combustion and the wedge angle inducing detonation on the minimum total pressure loss are also obtained. When the input energy is large and the wedge angle is small, the minimum total pressure loss point of oblique detonation wave will shift more easily to a large shock angle. Finally, according to the characteristics of the total pressure of oblique detonation, a simple design idea which can increase the theoretical upper limit of total pressure of the engine is presented. The law of total pressure of oblique detonation wave will provide conceptual design direction of oblique detonation engine.
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图 1 斜爆轰波与斜激波极曲线之间的差异
Figure 1. The difference between the polars of oblique detonation wave and oblique shock
图 4 极曲线图谱上的斜爆轰波强度规律(Q = 10)
Figure 4. The law for oblique detonation wave intensity on the polar curves (Q = 10)
图 5 总压损失极小值线(红色实线: Q = 2的斜爆轰波; 绿色实线: 斜激波)
Figure 5. The curve of minimum total pressure loss for oblique detonation wave (Q = 2, solid red line) and oblique shock wave (solid green line)
图 6 不同Q值下总压损失与激波角的关系(20°楔面角)
Figure 6. The relation between total pressure loss and shock angle at different Q values (when the wedge angle is 20°)
图 7 不同Q值下的最小总压损失和最弱爆轰波强度(20°楔面角)
Figure 7. The minimum total pressure loss and the weakest detonation wave strength at different Q values (when the wedge angle is 20°)
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