火箭推进2025，Vol.51Issue(6)：77-86,96,11.DOI:10.3969/j.issn.1672-9374.2025.06.008
环形冲压燃烧室环缝式与发散孔式气膜冷却效果对比
Comparison on the cooling effect of annular slot-type and effusion hole-type film-cooling in annular ramjet combustion chamber
摘要
Abstract
To investigate the cooling characteristics of different film cooling schemes under high-Mach-number operating condition of annular ramjet combustion chamber,annular slot-type and effusion hole-type film cooling schemes were designed.Using the heat-liquid-solid coupling method,numerical simulations were conducted to investigate the flow and heat transfer characteristics of the film cooling.The cooling effectiveness of two cooling configurations was analyzed under a flight condition of 4.5Ma,with average blowing ratios of 0.50,0.75,1.00 and 1.50.The results indicated that the cooling efficiency was significantly improved when the blowing ratio was increased from 0.50 to 0.75 under both cooling configurations,while the improvement of cooling efficiency was not significant when it was increased from 0.75 to 1.50.The effusion hole-type exhibited a high-temperature region near the leading edge due to the incomplete coolant film establishment during the initial cooling process.The temperature distribution of the annular-slot type demonstrated a sawtooth pattern,the lowest temperature occurring at slot exits,culminating in peak temperatures at each panel's trailing edge.Comparative analysis revealed that when the blowing ratios is less than 0.75,the effusion hole-type achieved slightly lower average wall temperatures than the annular slot-type while maintaining the superior temperature uniformity.When the blowing ratio exceeded 1.00,the annular slot-type demonstrated better overall cooling performance in terms of average wall temperature,though the effusion hole-type retained effective cooling capability in the combustor's downstream region.Therefore,it is more suitable to adopt a effusion hole cooling structure under low blowing ratio conditions.关键词
环形冲压燃烧室/气膜冷却/热流固耦合/吹风比/环缝式/发散孔Key words
annular ramjet combustion chamber/film-cooling/heat-liquid-solid coupling/blowing ratio/annular slot-type/effusion hole分类
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王晨阳,谭建国,张冬冬..环形冲压燃烧室环缝式与发散孔式气膜冷却效果对比[J].火箭推进,2025,51(6):77-86,96,11.基金项目
中国科协青年人才托举工程(2022QNRC001) （2022QNRC001）
国家自然科学基金(12002372) （12002372）
湖南省自然科学基金(2021JJ40674). （2021JJ40674）
