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作 者:吕玉妹 王建华[1] 伍楠 吴万范 贺菲[1] 麻玉龙 LYU Yumei;WANG Jianhua;WU Nan;WU Wanfan;HE Fei;MA Yulong(CAS Key Laboratory of Mechanical Behavior and Design of Materials,Department of Thermal Science and Energy Engineering,University of Science and Technology of China,Hefei 230027,China;School of Mechatronic Engineering and Automation,Foshan University,Foshan 528000,China)
机构地区:[1]中国科学技术大学热科学和能源工程系中国科学院材料力学行为和设计重点实验室,安徽合肥230027 [2]佛山大学机电工程与自动化学院,广东佛山528000
出 处:《推进技术》2024年第7期153-160,共8页Journal of Propulsion Technology
基 金:国家重点研发计划(2022YFB3707000);国家自然科学基金(52006149)。
摘 要:面对超燃冲压发动机燃烧室严峻热环境,需要通过改进设计以提高气膜冷却性能。本文用数值方法分析比较了三种不同于传统气膜冷却的结构:(1)沿冷气通道增加气膜孔直径的改进型气膜冷却结构;(2)增加冷气冲击与对流换热的层板冷却结构;(3)增加多孔板的发散气膜组合冷却结构。通过机理实验数据验证数学模型和数值方法。利用经过验证的模型和方法,在真实的超燃冲压发动机燃烧室工况下,数值分析三种结构的冷却机理。在不同冷气注射量下,比较三种冷却结构热端冷却效率及温度分布的均匀性,结果表明组合冷却结构最高冷却效率高出其他结构的28%。此外,分析热障涂层对三种结构综合冷却特性的贡献,结果表明层板结构冷却效率在大冷气量下高出其他结构的16%。It is necessary to promote the performance of film cooling by improving the design in the severe thermal environment of scramjet combustor.Herein,three different structures from traditional film cooling struc-ture are analysed and compared by numerical method.(1)Improved film cooling structure by increasing the diam-eter of the film hole along the cooling air passage;(2)The laminated cooling structure added cooling air impinge-ment and heat convection;(3)The transpiration film combined cooling structure with porous plate.The mathe-matical model and numerical method are verified by the experimental data of the mechanism.Based on the veri-fied model and method,the cooling mechanism of the three structures is analysed numerically under the real sc-ramjet combustor conditions.The cooling efficiency and the uniformity of temperature distribution on the hot end of the three structures are compared under different mass flux rate of cooling air,the results uncover that the max-imum cooling efficiency of the combined cooling structure is 28%higher than other structures.In addition,the contribution of the thermal barrier coating to the comprehensive cooling characteristics of the three structures is analysed,and the results reveal that the cooling efficiency of the laminated structure is 16%higher than that of other structures under a large amount of cooling air.
关 键 词:超燃冲压发动机 燃烧室 气膜冷却 层板冷却 发散气膜组合冷却 冷却效率 适用性
分 类 号:V231.1[航空宇航科学与技术—航空宇航推进理论与工程]
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