The Confirmation of Thermal Boundary Parameters in an Oxygen Kerosene Fuel-Rich Rocket Engine
The Confirmation of Thermal Boundary Parameters in an Oxygen Kerosene Fuel-Rich Rocket Engine
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DOI：
10.3390/aerospace9070343
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发表时间：
2022-06
期刊：
影响因子：
2.6
通讯作者：
Xiang-geng Wei;Zhong-dong Yang;Shaohua Zhu;Zhixin Zhao;Jinying Ye;O. Haidn
中科院分区：
文献类型：
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作者：
Xiang-geng Wei;Zhong-dong Yang;Shaohua Zhu;Zhixin Zhao;Jinying Ye;O. Haidn
热环境是液体火箭设计中的一个重要因素。本文对总流量为120g/S、氧燃比为1：1的GOX/煤油液体火箭发动机的边界热特性进行了理论分析、数值模拟和实验测试。用热电偶测量了燃烧室不同位置的轴向温度，用流量计测量了热流密度。我们发现，当碳层存在时，182 mm处的热流密度增加了6.8%。对于理论计算结果，用积碳体积分数修正导热系数后，理论热流密度(1.11 mW/m~2)和数值计算结果(0.89 mW/m~2，考虑喷油器)与实验值(0.937 mW/m~2)基本一致。本研究验证了这种情况下理论计算和模拟计算的准确性，为今后的数值计算提供了验证数据，也为气相模拟中壁面温度的设定提供了数据。
The thermal environment is an important factor in the design of liquid rockets. In this paper, theoretical analysis, numerical simulation and experimental testing are conducted to study the boundary thermal characteristics of a GOX/kerosene liquid rocket motor with a total flow rate of 120 g/s and an oxygen-fuel ratio of 1:1. We measured the axial temperature in different positions in the combustor using thermocouples and the heat flux using a flux meter. We found that the heat flux at 182 mm increases by 6.8% when a carbon deposit exists. For the theoretical results, after correcting the thermal conductivity by the volume fraction of carbon deposition, the theoretical heat flux (1.11 MW/m2, using the corrected thermal conductivity) and the numerical result (0.89 MW/m2, considering the injectors) are similar to the experimental value (0.937 MW/m2). This study validates the accuracy of theoretical and simulation calculation in this case, and provides verification data for future numerical calculation, as well as data for setting gas temperature at the wall in the simulation of the gas phase.