关键词: 冲击冷却;旋转; 涡轮叶片冷却;航空推进;换热特性;流动特性; 

Abstract: In order to obtain the rule of flow and heat transfer of “impingement-film cooling” configuration in limited space of rotating blade, numerical investigation was carried out to study the effects of jet Reynolds numbers Re_j, rotation numbers Ro and wall-to-jet temperature difference ratios (T_w-T_f)/T_w. The results show that in the cooling cell, there is deflexion of impinging flow,secondary flow due to Coriolis and centrifugal forces and so on. Besides, the limited space and sparse film cooling stream can increase high heat transfer coefficient on the stagnation point of impingement. Moreover, rotation negative effects to impingement is stronger with same direction impingement (in basin region) than with reverse direction impingement (in back region).Finally, the results about Nu with varying condition of rotation prove that the structure with limited space and sparse film holes can leash the reduction of efficiency of heat transfer due to the rotation.

Key words: Impinging cooling; Rotation; Cooling of turbine blade; Aerospace propulsion system; Heat transfer characteristic; Fluid characteristic