Analysis of Turbine Blade Cooling Based on Fluid Network Method

The high pressure(HP) turbine blade cooling configuration of the E3 aircraft engine was analyzed by using fluid network method.The fluid network was created with proper simplification of the cooling configuration and selection of components models.Flow fields of the HP turbine stage were calculated to get the required data at the numerical boundaries in the fluid network.Loss coefficients and heat transfer coefficients for the components involved were determined through experimental correlations,and characteristic curves customized by the authors.Comparisons between the present results and the data from the NASA report show that the present method can predict the coolant mass flow rates,temperatures and pressure of the network branches very well.This method can be used for the analysis of blade cooling performance and for the preliminary cooling design.