Numerical Analysis of Heat Exchange and Pressure Loss in Flow inside Ribbed Channels and in Turn Legs of Cooling Systems of Gas Turbine Blades

Results of numerical calculation of heat withdrawal and pressure loss in turn legs of the loop cooling circuit of gas turbine blades are given. The numerical model verification is conducted for Reynolds numbers in the range from 1.5×10⁴ to 10⁵. The influence of the guiding-element geometry on the pressure loss coefficient is demonstrated and the channel geometry is defined which provides the undetached flow and the loss reduction in the turns. Results of the combined approach to the heat withdrawal calculation at the turn leg of the cooler are presented.