Optimal design of composite turbine blade using genetic algorithms

The present paper proposes the use of genetic algorithms (GAs) for the optimal design (cost effective) of a composite turbine blade made of layers of several materials. The coupling of in-plane and twisting stiffnesses in general laminates is made use of to design the turbine blade. The optimized blade will have minimal twisting curvature, reduced twisting vibrations of the blade and consequent less turbulence in the working fluid. A simplified design method is developed to determine the optimum combination of layer materials, layer orientations, layer thicknesses and laminate configuration, With the assumption of the turbine blade as a flat plate for the purpose of analysis, the use of the genetic algorithm is illustrated with examples of blades of 12, 24 and 36 layered composites. The discreteness of the search space makes GAs particularly suitable to use in this problem.