Investigation of the effects of rib application on cooling in a turbine blade

Turbine blades are system components exposed to extremely high temperatures. Effective cooling of turbine blades is essential to enhance efficiency and extend the operational lifespan of gas turbines. In this study, a new rib turbulator cooling design was tested for the NASA C3X turbine blade. The analyses were compared with those conducted on non-ribbed blades. According to the findings, an average surface temperature of 574.6 K and a maximum surface temperature of 661.8 K were achieved. These values indicate a cooling efficiency of 19.1% for the leading edge, which is exposed to the maximum temperature, and 29.75% for the average surface temperature. All data obtained from the study have been shared in the form of figures and graphs.