Optimization procedure of blade cooling system

This paper discuses the problem of cooling system optimization within a gas turbine vane. The analysis involves the optimization of the location and size of internal cooling passages (circular and noncircular) within the vane. Shape of a noncircular passage is modelled with Bezier's splines. The analysis is performed by means of the genetic algorithm for the optimization task and FEM for heat transfer predictions within the component. In the present study the vane profile is assumed as aerodynamically optimal.