Optimization of the cooling system of the nozzle blade of an energy gas turbine
The system of convective-film cooling of the first stage nozzle blade of the gas turbine is optimized on the basis of a unified information environment with the inclusion of an effective optimization method using the response surface, an indirect optimization algorithm based on the principles of self-organization (IOSO). The paper proposes a mathematical model for calculating the wall temperature during convective film cooling based on empirical data to determine the heat transfer coefficient and the efficiency of film cooling. A single code has been developed that allows combining a FORTRAN program for calculating the cooling depth of a perforated plate and an IOSO optimizer. The calculation results indicate a decrease in the relative flow rate of the cooler (from 7% to 6%) due to the newly obtained distributions of the cooler flow rate, the diameter of the blow holes and the pitch of the perforation system (with an average cooling depth of 0.65). Thus, it is possible to increase the power of the gas turbine by 160 kW.