基于双层壁冷却结构的综合冷效数值解耦研究
Numerical decoupling of overall cooling effectiveness based on double-wall cooling structure
刘润洲 1李海旺 1由儒全 1黄毅 1陶智2
作者信息
- 1. 北京航空航天大学航空发动机研究院,北京 102206;北京航空航天大学航空发动机气动热力国家级重点实验室,北京 102206
- 2. 北京航空航天大学航空发动机研究院,北京 102206;北京航空航天大学能源与动力工程学院,北京 102206;北京航空航天大学航空发动机气动热力国家级重点实验室,北京 102206
- 折叠
摘要
采用数值解耦的方法,定量分析了双层壁平板冷却结构的综合冷效与内部冷却、气膜孔内冷却和冷气覆盖之间的关系.吹风比为0.25、0.5、1和1.5.通过研究发现,吹风比对双层壁模型的综合冷效有明显影响.当吹风比由0.25增大到1.5时,综合冷效增大57.9％.内部冷却占主导地位的区域主要是冲击气流的驻点区.气膜孔内冷却影响最大的区域为气膜孔出口的上游,而且沿流向孔内冷却的影响逐渐减小.冷气覆盖对综合冷效的影响沿流向逐渐积累,在第3个气膜孔出口附近冷气覆盖的影响最大.而且在冷气覆盖区域的影响要大于在远离气膜孔区域的影响.当吹风比增大至1时,孔内冷却对综合冷效的影响已经超过了冷气覆盖.
Abstract
Numerical decoupling method was used to quantitatively analyze the relationship between the overall cooling effectiveness of impingement-effusion model and the internal cooling,bore cooling and coolant coverage.The blowing ratios were 0.25,0.5,1 and 1.5.It was found that the blowing ratio had a significant effect on the comprehensive cooling effect of the impact divergence model.When the blowing ratio increased from 0.25 to 1.5,the overall cooling effectiveness increased by 57.9％.The stagnation region of impingement jet was mainly dominated by internal cooling.The region where the bore cooling had the greatest influence on the overall cooling effectiveness was located upstream of the film hole outlet,and the influence of bore cooling along the streamwise direction was gradually reduced.The influence of coolant coverage on the overall cooling effectiveness gradually accumulated along the streamwise direction,and the influence near the third film hole outlet was the largest.The influence in the downstream of film hole was greater than that in the region away from the film hole.When the blowing ratio increased to 1,the effect of bore cooling on the overall cooling effectiveness exceeded that of coolant coverage.
关键词
综合冷效/气膜冷却/内部冷却/解耦/吹风比/平板模型Key words
overall cooling effectiveness/film cooling/internal cooling/decoupling method/blowing ratio/flat-plate model引用本文复制引用
基金项目
国家科技重大专项(2017-Ⅲ-0010-0036)
北京市自然科学基金(3222034)
先进航空动力创新工作站项目(HKCX2022-01-007)
出版年
2024
NETL
NSTL
万方数据