Development of the cooling system and verification of results of the modeling of the temperature state of the gas turbine blade

The article presents a complex of calculation and design works on the development of a highly efficient cooling system for blades of high-temperature gas turbines for modern gas turbine engines. The analysis of the results of experimental studies on the efficiency of the convective-film cooling system of the blades is carried out, as well as the fault defection of these blades, during which multiple cracks on the exit edge are revealed. Therefore the design of the blade of the high-pressure turbine has been modified, during this a three-dimensional approach to modeling the thermal state of the blade with the solution of the coupled interfaced heat conduction problem is proposed for use. For the purpose of determination of throughput capacity and control of stability of the production of the modified blade, the purge of the cooled channels and openings of the perforation rows is carried out. On the basis of the results of experimental studies, a mathematical model of the purge test stand based on ANSYS CFX packages corresponding to the actual dimensions is designed. The total air flow rate at the open and closed openings of the perforation rows, as well as at the open and closed slots in the exit edge of the blade is calculated in the CFX-Solver Manager program. On the basis of gas-dynamic and hydraulic calculations, three-dimensional thermal calculations using boundary conditions of the third kind are performed in the ANSYS ICEM CFD package and the thermal models of the blades are obtained. Also the fields of cooling efficiency for separate sections of the blade of the first stage of the high-pressure turbine are obtained. The verification of the thermal state of this blade on the cross sections is carried out on the basis of the results of temperature measurement at the maximum modes of the gas generator tests on the gas test stand. The improved engineering calculating method allows to refine the prediction of the thermal state of the blade and also to carry out design of cooling systems of the gas turbine blades for modern gas turbine engines.