超燃冲压发动机再生冷却结构的多目标优化设计

推进技术 ›› 2018, Vol. 39 ›› Issue (6): 1331-1339.

超燃冲压发动机再生冷却结构的多目标优化设计

秦昂¹,张登成¹,魏扬¹,周章文¹,张久星²

空军工程大学航空航天工程学院，陕西西安 710038,空军工程大学航空航天工程学院，陕西西安 710038,空军工程大学航空航天工程学院，陕西西安 710038,空军工程大学航空航天工程学院，陕西西安 710038,中国人民解放军93793部队，北京 102100

发布日期:2021-08-15
作者简介:秦昂，男，硕士生，研究领域为超燃冲压发动机的热防护。
基金资助:
陕西省工业科技攻关项目(2015GY098)。

Multi-Objective Optimization on Regenerative Cooling Structure of Scramjet

School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China,School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China,School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China,School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China and Unit 93793 of PLA，Beijing 102100，China

Published:2021-08-15

摘要/Abstract

摘要： 针对当前超燃冲压发动机再生冷却结构的优化研究存在对经验关联式依赖的问题，且对流动压力损失问题重视不足，采用响应面法结合多目标遗传算法，以燃气侧平均壁温和流动压力损失为优化目标，对单根再生冷却通道的肋高、槽宽和肋厚进行优化设计。结果表明:肋高对优化目标的影响程度最大，其次是槽宽、肋厚，且不同进口质量流量下设计变量对优化目标的影响规律是相似的。计算得到设计工况下的Pareto 最优解集后，从中可选取多组综合流动换热性能优于初始通道的结构。对解集中一组优化通道进行圆整并以进口质量流量为设计变量建立响应面，获得了冷却平板的设计方案及1.539～9.604kg/s的允许进口质量流量范围。

关键词: 超燃冲压发动机；再生冷却通道；响应面法；遗传算法；多目标优化

Abstract: Current optimization for regenerative cooling structure of scramjet depends on empirical relations， and insufficient attention is given to flow pressure loss. Optimal design of fin height， slot width， fin thickness of single regenerative cooling channel was carried out by the response surface methodology (RSM) combined with multi-objective genetic algorithm (MOGA) ， with the average wall temperature at the hot-gas side and flow pressure loss as optimization objective. The results show that the most sensitive design variable is fin height， and then the slot width， fin thickness， and the influence of design variable to optimization objective is the same at different inlet mass flow. After the Pareto optimal solution set in design condition is found， multiple structures can be obtained which performs better in the flow and heat transfer characteristic than the initial channel. Design program of cooling panel are obtained and the allowed range of inlet mass flow is found to be 1.539～9.604kg/s by rounding of one optimization channel and building response surface with the inlet mass flow as design variable.

Key words: Scramjet; Regenerative cooling channel; Response surface methodology; Genetic algorithm; Multi-objective optimization

秦昂,张登成,魏扬,周章文,张久星. 超燃冲压发动机再生冷却结构的多目标优化设计[J]. 推进技术, 2018, 39(6): 1331-1339.

QIN Ang¹,ZHANG Deng-cheng¹,WEI Yang¹,ZHOU Zhang-wen¹,ZHANG Jiu-xing². Multi-Objective Optimization on Regenerative Cooling Structure of Scramjet[J]. Journal of Propulsion Technology, 2018, 39(6): 1331-1339.

参考文献

[1] Qin J, Bao W, Zhou W, et al. Performance Cycle Analysis of an Open Cooling Cycle for a Scramjet[J]. Journal of Aerospace Engineering, 2009, 223(6): 599-607.
[2] Parris D K, Landrum D B. Effect of Tube Geometry on Regenerative Cooling Performance[R]. AIAA 2005-4301.
[3] Zhang Silong, Feng Yu, Zhang Duo. Parametric Numerical Analysis of Regenerative Cooling in Hydrogen Fueled Scramjet Engines[J]. International Journal of Hydrogen Energy, 2016, 41(25): 10942-10960.
[4] 牛禄, 程惠尔, 李明辉. 高宽比和粗糙度对再生冷却通道流动的影响[J]. 上海交通大学报, 2002, 36(11): 1612-1615.
[5] 吴峰, 王秋旺, 罗来勤, 等. 液体火箭发动机推力室冷却通道传热优化计算[J]. 推进技术, 2006, 27(3): 197-200. (WU Feng, WANG Qiu-wang, LUO Lai-qin, et al. Numerical Optimization Simulation on Heat Transfer in Cooling Channel of H2/O₂ Liquid Rocket Engine Thrust Chamber[J]. Journal of Propulsion Technology, 2006, 27(3): 197-200.)
[6] 鲍文, 周伟星, 周有新. 超燃冲压发动机再生冷却结构的强化换热优化研究[J]. 宇航学报, 2008, 29(1): 246-251.
[7] 王厚庆, 何国强, 刘佩进, 等. 超燃冲压发动机燃烧室新型热结构的优化设计[J]. 推进技术, 2009, 30(3): 263-266. (WANG Hou-qing, HE Guo-qiang, LIU Pei-jin, et al. Optimized Design on a New Type Thermal Structure of Scramjet Combustor[J]. Journal of Propulsion Technology, 2009, 30(3): 263-266.)
[8] Zhang S, Qin J, Xie K, et al. Thermal Behavior inside Scramjet Cooling Channels at Different Channel Aspect Ratios[J]. Journal of Propulsion and Power, 2015, 32(1): 57-70.
[9] Youn B, Mills A F. Flow of Supercritical Hydrogen in a Uniformly Heated Circular Tube[J]. Numerical Heat Transfer, Part A: Applications, 1993, 24(1): 1-24.
[10] Youn B, Mills A F. Cooling Panel Optimization for the Active Cooling System of a Hypersonic Aircraft[J]. Journal of Thermophysics and Heat Transfer, 1995, 9(1): 136-143.
[11] Zhong F Q, Fan X J, Yu G, et al. Heat Transfer of Aviation Kerosene at Supercritical Conditions [R]. AIAA 2008-4615.
[12] 郑力铭, 孙冰. 超燃冲压发动机二维热环境数值模拟[J]. 航空动力学报, 2007, 22(5): 823-828.
[13] 徐自立. 高温金属材料的性能、强度设计及工程应用. [M]. 北京:化学工业出版社, 2006.
[14] 王彦红, 李素芬, 东明. 方形再生冷却通道内超临界正癸烷湍流传热数值研究[J]. 推进技术, 2015, 36(11): 1669-1676. (WANG Yan-hong, LI Su-fen, DONG Ming, et al. Numerical Study on Turbulent Heat Transfer of Supercritical n-Decane in a Square Regenerative Cooling Channel[J]. Journal of Propulsion Technology, 2015, 36(11): 1669-1676.)
[15] 李中洲, 朱惠人, 张霞. 微小圆管内煤油流动研究[J]. 航空动力学报, 2010, 25(8): 1728-1732.
[16] 秦昂, 周章文, 张登成, 等. 再生冷却结构参数对煤油流动换热的影响及优化[J]. 空军工程大学学报:自然科学版, 2017, 18(4): 7-11.
[17] 胡俊峰, 徐贵阳, 郝亚洲. 基于响应面法的微操作平台多目标优化[J]. 光学精密工程, 2015, 23(4):1096-1104.
[18] 邓磊, 乔志德, 杨旭东, 等. 基于响应面法的低速翼型气动优化设计[J]. 空气动力学学报, 2010, 28(4): 430-435.
[19] 陶文铨. 传热学[M]. 西安:西北工业大学出版社, 2006.
[20] 周有新. 超燃冲压发动机再生主动冷却结构强化换热分析与设计[D]. 哈尔滨:哈尔滨工业大学, 2007.(编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2017-05-16；修订日期:2017-07-10。基金项目:陕西省工业科技攻关项目(2015GY098)。作者简介:秦昂,男,硕士生,研究领域为超燃冲压发动机的热防护。E-mail: 18682931162@163.com