Numerical analysis of the influence of turbulators constructive features on heat transfer in gas turbine blade cooling channels

摘要

In the present study, the influence of turbulators constructive features on heat transfer in gas turbine blade cooling channels has been investigated by analyzing the results of numerical modelling. The numerical model has been verified by experimental data. The radial channel of the leading edge with the heat transfer turbulators in the form of ribs was the first object of a numerical study. Three options of the rib design were investigated: with the sharp edges of all rib surfaces, with the rounded end surfaces of the ribs and with end rounding of the top and side rib surfaces. Additionally, an option with ribs installed at an angle of 45° relatively to the flow direction was studied. A convergent channel of the blade trailing edge with one and half-pass cooling channel was the second object of a numerical investigation. Effect of an angle of the coolant flow incidence on heat transfer for staggered pin fin array has been analyzed. A semicircular cross-section channel with the coolant radial flow, in which the air supply was carried out through circular holes was the last research object. A cross flow influence on thermal and hydraulic characteristics has been investigated.