Aero-thermal coupled through-flow method for cooled turbines with new cooling model

Abstract

The aero-thermal-coupled phenomenon is significant in modern cooled turbines, and an aero-thermal coupled throughflow method has previously been developed by the authors for considering the influence of heat transfer and coolant mixing in through-flow design. However, the original cooling model is not capable of calculating the distribution of the coolant mass flow rate and pressure loss in complex cooling structures. Therefore, in this paper, a one-dimensional flow calculation for the internal coolant is introduced into the heat transfer calculation to further improve the through-flow cooling model. Based on various empirical correlations, the cooling model can be used to simulate different cooling structures, such as ribbed channels and cooling holes. Three operating conditions were selected for verification of the NASA-C3X vane, which has 10 internal radial cooling channels. The calculated Nusselt number of internal cooling channels strongly agrees with the experimental data, and the predicted blade surface pressure and temperature distributions at mid span are also in good agreement with the experimental data. The convergence history of the meridional velocity and blade surface temperature demonstrates effective convergence properties. Therefore, the aero-thermalcoupled through-flow method with the new cooling model can provide a reliable tool for cooled turbine through-flow design and analysis.

Heat transfer characteristics of a dimpled/protrusioned pin fin wedge duct with different converging angles for turbine blades

“…Generally, the blades and hubs of a gas turbine usually have to bear an increasing temperature in order to improve the thermal efficiency of the aero-engine [1,2]. Because of the limitation of the sustainable temperature of the metal materials, cooling strategies of the turbine are becoming more and more important and highlighted.…”