Experimental and numerical study of enhanced composite cooling structure with ribs and pin-fins in a Heavy Duty Gas Turbine Blade

In order to obtain high-efficiency heat transfer for heavy-duty gas turbines, the internal enhanced composite cooling of turbine blades has been investigated. The results of transient liquid crystal experiments indicate that as the Reynolds number increases, both continuous V-rib and broken V-rib exhibit stronger heat transfer performance, with the average heat transfer effect of continuous V-rib surpassing that of intermittent V-rib by approximately 6.4%. Subsequently, four V-rib structures including continuous, broken, and staggered configurations were analyzed using numerical simulation methods to demonstrate local three-dimensional turbulence characteristics and reveal the impact of V-rib parameter variations on heat transfer performance. The findings suggest that continuous V-rib exhibits superior Nusselt number, flow resistance, and comprehensive heat transfer performance compared to broken V-rib; while staggered V-rib demonstrates the highest flow resistance.