Gas turbine blades are subjected to elevated heat loads due to highly turbulent hot gases exiting the combustor section. Several internal and external cooling techniques are used to protect the blades from such hostile environment. Trailing edge of a turbine blade is usually cooled with array of staggered cylindrical pins, which connects the pressure and suction side internal walls and hence provide improved structural integrity. However, the heat transfer enhancement levels for array of pin-fins is generally lower than jet impingement and ribbed channels. In this study, we present a three-tier impingement cooling design for blade trailing-edge and part of mid-chord region. In this design, pressure and suction side internal walls are subjected to oblique jet impingement. Three different configurations have been studied where we have systematically varied the jet diameters and number of jets in an array for different tiers. Numerical simulations have been carried out for different flow conditions, which corresponds to Reynolds numbers (based on 1st-passage jet diameter) ranging between 3000 and 46000. First two plenums had high levels of heat transfer due to oblique jet impingement, where the suction side internal wall representative surface, had higher heat transfer compared to the pressure side internal wall. Third tier had the lowest heat transfer due to triangle-like configuration where jets were almost parallel to pressure and suction side surfaces, and hence their effectiveness was lower than the oblique jet impingement in upstream two tiers.
Three-Tier Impingement Cooling Design for Gas Turbine Blade Trailing Edge
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Ramakrishnan, KR, Singh, P, & Ekkad, SV. "Three-Tier Impingement Cooling Design for Gas Turbine Blade Trailing Edge." Proceedings of the ASME 2018 International Mechanical Engineering Congress and Exposition. Volume 8B: Heat Transfer and Thermal Engineering. Pittsburgh, Pennsylvania, USA. November 9–15, 2018. V08BT10A030. ASME. https://doi.org/10.1115/IMECE2018-86430
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