摘要
为实现火箭基组合循环(RBCC)发动机宽域工作的稳定性和高效性,采用一维分析方法研究了宽域条件下燃烧室释热分布对RBCC发动机性能的影响规律。结果表明,在燃烧室中形成集中的释热分布有利于提升RBCC发动机的性能,但最短的释热区间长度受到进气道抗反压能力的制约,来流速度越高则允许的释热区间长度越短。通过地面试验对数值仿真结果进行验证,并基于瑞利概率密度函数和幂函数,建立了来流条件、发动机构型等因素与数值模拟释热率分布的关系式,验证集内预测曲线与原数据的相关系数均在0.9以上,可用于RBCC发动机性能的快速预示。
To achieve stability and efficiency in the wide-speed-range operation of rocket based combined cycle(RBCC)engines,one-dimensional analysis was used to study the influence of combustion chamber heat release distribution on RBCC engine performance under wide range conditions.The results indicate that the formation of a concentrated heat release distribution in the combustor is beneficial for improving the performance of RBCC engines,but the shortest heat release interval length is constrained by the anti backpressure ability of the inlet,and the allowable heat release interval length is shorter when the inflow velocity is higher.The numerical simulation results were verified through ground experiments,and the relationship between the inflow conditions,engine configuration,and the distribution of heat release rate in the numerical simulation was established using Rayleigh probability density function and power function.The correlation coefficients between the predicted curves within the validation set and the original data are all above 0.9,which can be used for rapid prediction of RBCC engine performance.
作者
朱润童
尹竣
葛保聪
安健
朱韶华
秦飞
ZHU Runtong;YIN Jun;GE Baocong;AN Jian;ZHU Shaohua;QIN Fei(College of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;Neimeng Power Machinery Institute,Hohhot 010010,China)
出处
《固体火箭技术》
北大核心
2025年第2期242-252,共11页
Journal of Solid Rocket Technology
基金
国家自然基金青年基金项目(52106165)。
