Analysis of the maximum flight Mach number of hydrocarbon-fueled scramjet engines under the flight cruising constraint and the combustor cooling requirement
Analysis of the maximum flight Mach number of hydrocarbon-fueled scramjet engines under the flight cruising constraint and the combustor cooling requirement
复制标题
飞行巡航约束下碳氢超燃冲压发动机最大飞行马赫数及燃烧室冷却要求分析
DOI：
10.1016/j.ast.2019.105594
复制
发表时间：
2020-03
影响因子：
5.6
通讯作者：
Wen Bao
中科院分区：
文献类型：
--
作者：
Youyin Wang;Kunlin Cheng;Jingfeng Tang;Xiaoyong Liu;Wen Bao
超燃冲压发动机是高超声速飞行器的最佳推进系统，研究其最大飞行马赫数具有重要意义。研究了高超声速飞行器用双模超燃冲压发动机的飞行马赫数上限及其影响因素。建立了具有等面积加热过程的超燃冲压发动机性能分析模型、燃烧室冷却需求分析模型和超燃冲压发动机动力高超声速飞行器巡航模型。当自由飞行马赫数大于10时，碳氢燃料双模态超燃冲压发动机的比冲与液氧煤油火箭发动机的比冲相似。引入高超声速飞行器参考面积与超燃冲压发动机进气道捕获面积之比，建立了超燃冲压发动机与高超声速飞行器的尺寸关系。考虑到推力和阻力的平衡，高超声速飞行器参考面积与超燃冲压发动机进气道捕获面积的比值越小，高超声速飞行器能够巡航的飞行马赫数越高。当攻角为10度时，高超声速飞行器参考面积与超燃冲压发动机捕获面积之比应小于5. 5，以保证飞行器能在8马赫的速度下工作。燃烧室最大长径比用来表示主动冷却要求，当飞行马赫数大于9时，最大长径比小于5。减小燃烧室壁面热流密度，增加燃料热沉，有助于增大燃烧室许用长度，从而在满足热防护要求的前提下提高超燃冲压发动机的最大飞行马赫数。
Scramjet is the optimal propulsion system for hypersonic vehicles, and it is important to study its maximum flight Mach number. Upper limit and its influence factors of the flight Mach number of dual-mode scramjet used in hypersonic vehicles are investigated in this paper. Scramjet performance analysis model with the constant-area heating process, cooling requirement analysis model of the combustor and cruise model of the scramjet-powered hypersonic vehicle are established. Specific impulse of dual-mode scramjet engine with hydrocarbon fuel is similar to that of liquid oxygen kerosene rocket engine when the freestream Mach number is above 10. The ratio of hypersonic vehicle reference area to scramjet inlet capture area is introduced to establish the size relationship between the scramjet engine and the hypersonic vehicle. Considering the balance of thrust and drag, smaller ratio of hypersonic vehicle reference area to scramjet inlet capture area leads to higher flight Mach number that hypersonic vehicle can cruise. When the angle of attack is 10 degrees, the ratio of hypersonic vehicle reference area to scramjet capture area should be less than 5.5 to ensure that the vehicle can work at Mach 8. The maximum length to diameter ratio of the combustor is used to indicate active cooling requirements, and it is less than 5 under the cooling requirement when flight Mach number is above 9. Reducing the heat flux at the combustor wall and increasing the fuel heat sink is helpful to increase the allowable combustion chamber length, so as to increase the maximum flight Mach number of the scramjet engine on the premise of meeting thermal protection requirement.
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DOI：
10.2514/6.2003-7031
发表时间：
2003-12
期刊：
--
影响因子：
--
作者：
F. Falempin;L. Serre
通讯作者：
F. Falempin;L. Serre
改善变几何双模式燃烧室燃烧性能的数值与实验研究
影响因子：
5.6
作者：
Feng Shuo;Chang Juntao;Zhang Junlong;Zhang Chenlin;Bao Wen
通讯作者：
Bao Wen
影响因子：
1.9
作者：
P. J. Waltrup-
通讯作者：
P. J. Waltrup-
空气节流对双模态超燃冲压发动机燃烧室燃烧模态形成及转变影响的数值研究
影响因子：
5.6
作者：
Ye Tian;Shunhua Yang;Jialing Le
通讯作者：
Jialing Le
DOI：
10.2514/6.2002-5116
发表时间：
2002-09
期刊：
--
影响因子：
--
作者：
T. Sunami;Atsuo Murakami;K. Kudo;M. Kodera;M. Nishioka
通讯作者：
T. Sunami;Atsuo Murakami;K. Kudo;M. Kodera;M. Nishioka