A New Method to Calculate the Coolant Requirements of a High Temperature Gas Turbine Blade

Abstract

Earlier papers by the first author have described a computational method of estimating the cooling flow requirements of blade rows in a high temperature gas turbine, for convective cooling alone and for convective plus film cooling; this method of analysis and computation, when applied to the whole blade chord was compared with a well known semi-empirical method. In the current paper, a more sophisticated method is developed from the earlier work and is used to calculate the cooling flow required for a nozzle guide vane [the first blade row] of a high temperature gas turbine, with given inlet gas temperature and coolant inlet temperature. Now the heat flux through an elementary cross-sectional area of the blade, at given spanwise [y] and chordwise [s] locations, is considered, with a guessed value of the elementary coolant flow [as a fraction dΨ(s) of the external gas flow]. At the given s, integration along the blade length gives the blade metal temperatures at the outer and inner walls, Tbg[y] and Tbcl[y]. If the value of Tbg at the blade tip [y = H] is assumed to be limited by material considerations to Tbg,max then the elementary coolant flow rate may be obtained by iteration. Summation along the chord then gives the total coolant flow, for the whole blade. Results using the method are then compared with a simpler calculation applied to the whole blade, which assumes chordwise constant temperatures and constant selected values of cooling efficiency and film cooling effectiveness.