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Dimensioning of automated regenerative cooling: Setting of high-end experiment

机译：自动再生冷却的尺寸：高端实验的设置

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Regenerative cooling is widely used in high-pressure and high-thrust fuel-cooled rocket engines, also suitable for hypersonic structures. The propellant duality in terms of functions (fuel and coolant) makes the thermal and combustion management quite challenging. Dynamics of the system must be studied to develop regulation and control strategies which should be performed with a response time lower than the lowest characteristic time found in supersonic combustion ramjets, i.e. about 1 ms. The present work aims at setting experiments at lab scale by simplifying the additional difficulty of supersonic flow, to determine appropriate regulation dynamics for latter model and control developments. A combustion chamber was dimensioned with similitude rules in terms of heat flux density, conversion rate, chemical compositions, dynamics. Computational Fluid Dynamics and analytical calculations were developed to dimension the experimental bench. It was found that a pyrolysis rate up to 100% can be obtained using ethylene as fuel at 50 bar and 1200 K and with a residence time of about 100 s. Combustion with air (adiabatic flame temperature up to 2400 K) will provide the required heat flux density. The operating range in terms of fuel pressure (10-50 bar), of fuel mass flow rates (50-100 mg s(-1)) and of equivalence ratio (0.8 to 1.0) have been certified. (C) 2015 Elsevier Masson SAS. All rights reserved.
机译：蓄冷冷却被广泛用于高压和高推力的燃油冷却火箭发动机，也适用于高超音速结构。推进剂在功能（燃料和冷却剂）方面的双重性使热管理和燃烧管理颇具挑战性。必须研究系统的动力学，以开发调节和控制策略，该策略和控制策略的响应时间应低于超音速燃烧冲压喷气发动机的最低特征时间，即约1毫秒。本工作旨在通过简化超声速流动的额外难度，在实验室规模上进行实验，从而确定用于后者模型和控制开发的适当调节动力学。根据热通量密度，转化率，化学成分，动力学，用相似规则确定燃烧室的尺寸。开发了计算流体动力学和分析计算来确定实验台的尺寸。已经发现，使用乙烯作为燃料在50巴和1200K下且停留时间为约100s时，可以获得高达100％的热解速率。与空气燃烧（绝热火焰温度高达2400 K）将提供所需的热通量密度。通过了燃油压力（10-50 bar），燃油质量流量（50-100 mg s（-1））和当量比（0.8至1.0）的工作范围的认证。 （C）2015 Elsevier Masson SAS。版权所有。

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