Effect of cooling channel geometry on re-cooled cycle performance for hydrogen fueled scramjet
Effect of cooling channel geometry on re-cooled cycle performance for hydrogen fueled scramjet
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DOI：
10.1016/j.ijhydene.2010.04.033
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发表时间：
2010-07
影响因子：
7.2
通讯作者：
W. Bao;J. Qin;Weixing Zhou;D. Yu
中科院分区：
文献类型：
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作者：
W. Bao;J. Qin;Weixing Zhou;D. Yu
为满足吸气式高超声速飞行器的冷却要求，研制高吸热性能的燃料得到了广泛的应用。然而，为了减少冷却时的燃料流量，重新冷却循环已被提出用于再生冷却的超燃冲压发动机。反复使用燃料散热器（冷却能力），间接增加燃料散热器。研究了高超声速飞行器再冷却循环的参数敏感性分析。从水动力、热工、功率平衡和马赫数约束等方面，提出了矩形光滑壁管道不可压缩流动的翅片型解析模型。在此模型的基础上，讨论了再冷循环与蓄热循环冷却通道结构设计的差异，并引入了一种新的再冷循环优化指标。研究了循环性能对冷却通道几何形状的敏感性，并在满足约束条件的情况下获得了再冷循环的最佳性能。讨论了再冷循环和再生冷却对通道设计变量影响的差异。
Developing fuel with higher heat sink is widely carried out to meet the cooling requirement for an airbreathing hypersonic vehicle. However, a Re-Cooled Cycle has been newly proposed for a regeneratively cooled scramjet to reduce the fuel flow for cooling. Fuel heat sink (cooling capacity) is repeatedly used to indirectly increase the fuel heat sink. Parametric sensitivity analysis of Re-Cooled Cycle of a hypersonic aircraft is explored. An analytical fin-type model for incompressible flow in smooth-wall rectangular ducts in terms of hydrodynamic, thermal, power balance and Mach number constraints is proposed. Based on this model, the difference of the cooling channel structure design between Re-Cooled Cycle and regenerative cooling is discussed, and a new optimization index is introduced for Re-Cooled Cycle. The sensitivity of the cycle performance to cooling channel geometry is investigated, and the optimal performance of a Re-Cooled Cycle is obtained by satisfying constraints. The differences of the effect of channel design variables between Re-Cooled Cycle and regenerative cooling are also discussed.