致密多孔壁冷流入射角对冷却效果影响的数值研究  

Numerical Study of the Blowing Angle Effecton Effusi on Cooling Effectiveness

作　　者：胡娅萍[1] 吉洪湖[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《航空动力学报》2005年第1期116-119,共4页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目 ( 5 0 0 760 17) ;国家重点基础研究发展规划资助项目 ( G2 0 0 0 0 2 63 0 2 )

摘　　要：采用数值模拟方法研究了冷气流的入射角对致密多孔壁冷却效果的影响 ,通过 9个算例分析比较入射角为 3 0°,60°和 90°情况下的冷却效果 ,在每个入射下吹风比 M分别取为 0 .5 0 ,1 .0和 2 .0。结果表明 :随入射角的增大 ,冷却效果是降低的。无论 M为何值 ,入射角为 3 0°和 60°时 ,整个平壁上冷却效果的分布都很相似 ;而入射角为 90°时冷却效果的分布则不然 ,虽然与前者比较起来其冷却效果最差 ,但与常规气膜冷却相比 ,入射角为The influences of the coolant flow blowing angle a on the effusion cooling effectiveness of a porous plate were investigated. Nine cases were studied, which cover three blowing angles of α= 30°, 60°, 90° and for each angle three blowing ratios of M = 0.5, 1.0, 2.0. The results show that with the increase of the cooling effectiveness reduces for all the calculated cases. For cases of α = 30° and 60° the distribution of cooling effectiveness 7 along the whole plate are very similar for any given blowing ratio. While for the cases of α = 90°, the distributions of cooling effectiveness are quite different. Although the cooling effectiveness of the cases with α = 90° for any given blowing ratio is the worst among the three angles stated, its absolute value is still quite high compared with the conventional film cooling.

关 键 词：航空、航天推进系统 致密多孔壁冷却 入射角 吹风比 冷却效果 

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]