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首页> 外文期刊>Aerospace science and technology >Analysis of the maximum flight Mach number of hydrocarbon-fueled scramjet engines under the flight cruising constraint and the combustor cooling requirement
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Analysis of the maximum flight Mach number of hydrocarbon-fueled scramjet engines under the flight cruising constraint and the combustor cooling requirement

机译：巡航约束和燃烧室冷却要求下碳氢燃料超燃发动机的最大飞行马赫数分析

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摘要

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. (C) 2020 Elsevier Masson SAS. All rights reserved.
机译：Scramjet是超音速飞行器的最佳推进系统，研究其最大飞行马赫数非常重要。研究了高超声速飞行器双模超燃冲压发动机飞行马赫数的上限及其影响因素。建立了具有恒定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超音速飞行器的巡航模型。当自由流马赫数大于10时，含碳氢燃料的双模超燃冲压发动机的比冲与液态氧煤油火箭发动机的比冲相似。引入高超音速飞行器参考面积与超燃冲压发动机进气口捕集面积之比，建立两者之间的尺寸关系。超燃冲压发动机和超音速飞行器。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口捕获面积的比值较小，导致高超声速飞行器可以巡航的飞行马赫数更高。当迎角为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，以确保飞行器能够以8马赫的速度工作。燃烧室的最大长度与直径之比用于指示主动燃烧室。冷却要求，并且当飞行马赫数大于9时，在冷却要求下小于5。减少燃烧室壁的热通量并增加燃料散热器有助于增加允许的燃烧室长度，从而增加燃烧室长度。在满足热保护要求的前提下，超燃冲压发动机的最大飞行马赫数。 （C）2020年Elsevier Masson SAS。版权所有。

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