摘要
对席壁冷却结构的平板实验件进行热态实验研究,测定反映该冷却结构冷却效果的两个无因次温差比η和θ的大小随冷却密流man/A平板的变化规律,一方面以检验本席壁结构的冷却效果。
The values of the dimensionless temperature difference ratio η and θ depend on the thermal conductivity of multiple-duct wall,coolant mass flow per unit surface area and geometrical structure of the multiple-hole base.The values of η and θ demonstrate the cooling effect of a cooling structure to a certain extent. Hot state experimental investigation on a piece of experimental plate of mat-wall cooling structure has been done,and the values of η and θ and their variation with the cooling density flow that display the cooling effect of the cooling structure have been determined. The cooling effect of the mat-wall structure can be examined, which can offer support for seven-heat-flow wall temperature calculation.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1996年第1期18-23,共6页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金
关键词
席壁冷却结构
实验
无因次温差比
航空发动机
mat-wall cooling structure dimensionless temperature difference ratio experimental investigation cooling effect