Flow Mechanism and Heat Transfer Analysis on Ribbed/protruded Surface in Impingement/effusion Cooling of a Turbine Guided Vane Based on Conjugate Heat Transfer

In this study, the conjugate heat transfer method is employed to numerically investigate the thermal performance of the inner wall surface with different turbulators (i.e., ribs or protrusions) in a turbine guided vane. The effects of turbulators on flow and heat transfer are analyzed in detail, including their influence on pressure and velocity distributions, Nusselt number distributions, and flow fields. Through quantitative analysis, the results show that the introduction of ribs or protrusions dramatically increases the discharge coefficients of jet nozzles (by up to 71.5%) and the heat transfer (by up to 47.3%) between coolant and vane inner wall, while inhibiting the effusion of film holes, especially when ribs are adopted. Furthermore, all turbulators feature blockage effects on the flow of coolant, which can reduce the coolant assumption by up to 2.28%. A comparative analysis of various cooling structures reveals that the vane inner wall incorporating orthogonal ribs and protrusions exhibits the highest overall cooling effectiveness, exceeding that of the vane inner wall without turbulators by 0.0249. These findings provide valuable guidance for the design and optimization of advanced cooling structures in turbine blades.