摘要
为满足某大型液体火箭贮箱增压介质加热需求,对火箭上常用的多层嵌套钎焊铣槽式换热器结构特点进行了分析,对影响传热计算准确性的主要因素进行了剖析,建立了一维数学仿真传热模型,针对局部两相流换热采用了简化计算模型。换热器试验结果表明:传热计算结果与试验结果一致性较好,表明了传热模型建立的合理性;基于试验数据,对两相流简化计算模型进行了修正,拓宽了传热模型的适用性和计算的准确性。修正后的传热模型可用于多层嵌套钎焊铣槽式换热器或类似结构换热器的初步优化设计。
In order to meet the heating requirements of pressurized medium in the tank of a large liquid rocket,the structural characteristics of multi-layer brazed milling groove heat exchangers commonly used in rockets were analyzed.By analyzing the main factors affecting the accuracy of heat transfer calculation,a one-dimensional mathematical simulation heat transfer model was established,and a simplified calculation model was adopted for the heat transfer of local two-phase flow.The experimental results of heat exchanger show that the heat transfer calculation results are in good agreement with the experimental data,which indicates the rationality of the heat transfer model.Based on the experimental data,the simplified calculation model of two-phase flow is modified,which broadens the applicability of the heat transfer model and improves the calculation accuracy.The modified heat transfer model can be used for the preliminary optimization design of multi-layer brazed milling groove heat exchangers or heat exchangers with similar structures.
作者
刘军彦
王玫
田雅洁
杨永强
霍世慧
LIU Junyan;WANG Mei;TIAN Yajie;YANG Yongqiang;HUO Shihui(Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)
出处
《火箭推进》
CAS
2022年第4期51-58,共8页
Journal of Rocket Propulsion
基金
国家自然科学基金(52005385)。
关键词
火箭发动机
换热器
传热计算
仿真模型
rocket engine
heat exchanger
heat transfer calculation
simulation model
