Parametric performance analysis of multiple Re-Cooled Cycle for hydrogen fueled scramjet
Parametric performance analysis of multiple Re-Cooled Cycle for hydrogen fueled scramjet
复制标题
氢燃料超燃冲压发动机多次再冷循环参数性能分析
DOI：
10.1016/j.ijhydene.2009.06.006
复制
发表时间：
2009-09
影响因子：
7.2
通讯作者：
Yu, Daren
中科院分区：
文献类型：
--
作者：
Qin, Jiang;Bao, Wen;Zhou, Weixing;Yu, Daren
提出了一种用于再生冷却超燃冲压发动机的再冷却循环，以减少氢燃料的冷却流量。在完成第一次冷却后，氢燃料可以通过将焓从燃料传递到功而用于二次冷却。因此，重复使用燃料散热器（冷却能力）来间接增加燃料散热器。该方法不需要携带多余的燃料进行冷却或寻找新的冷却剂，而是减少了冷却燃料流量，使机载燃料足以满足整个高超声速飞行器的冷却要求。结合超燃冲压发动机的特点，定义了两个新的性能参数，讨论了RCC循环与膨胀机循环的区别，并考虑了冷却通道的压力损失。对多种RCC进行了性能比较，初步探讨了RCC在超燃冲压发动机上的应用局限性和真实的可能性。
A Re-Cooled Cycle is newly proposed for a regeneratively cooled scramjet to reduce the hydrogen fuel flow for cooling. Upon the completion of the first cooling, hydrogen fuel can be used for secondary cooling by transferring the enthalpy from fuel to work. Fuel heat sink (cooling capacity) is thus repeatedly used to indirectly increase the fuel heat sink. Instead of carrying excess fuel for cooling or seeking for any new coolant, the cooling fuel flow is reduced, and fuel onboard is adequate to satisfy the cooling requirement for the whole hypersonic vehicle. Two new performance parameters are defined combining the characteristics of scramjet, differences between RCC and expander cycle is discussed, and pressure loss in cooling passage is also considered. Performance comparison is carried among multiple RCCs, and preliminary application limit and real possibility of RCC for scramjet is discussed.
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DOI：
10.2514/6.1998-3734
发表时间：
1998-07
期刊：
--
影响因子：
--
作者：
Felix F. Chen;W. Tam;N. Shimp;R. Norris
通讯作者：
Felix F. Chen;W. Tam;N. Shimp;R. Norris
影响因子：
10.4
作者：
Yu, Daren;Bao, Wen;Zhou, Weixing;Qin, Jiang
通讯作者：
Qin, Jiang
影响因子：
2.1
作者：
B. Youn;A. F. Mills
通讯作者：
B. Youn;A. F. Mills
影响因子：
1.9
作者：
T. Kanda;G. Masuya;Y. Wakamatsu;N. Chinzei;A. Kanmuri
通讯作者：
T. Kanda;G. Masuya;Y. Wakamatsu;N. Chinzei;A. Kanmuri
影响因子：
1.9
作者：
J. M. Locke;D. Landrum
通讯作者：
J. M. Locke;D. Landrum