Design optimization of compressor blades using parallel genetic algorithms

Simple Genetic Algorithm is improved with Niche and adaptive operator,the new algorithm called Improved Genetic Algorithm(IGA) is parallelized using WinSock,multithread and Client-Server architecture.Blade profiles are parameterized using Hicks Henne function,2D cascade flow fields are calculated by using NavierStokes equation method.To form software for design optimization of compressor blade profiles,the IGA is combined with the above blade profile parameterization and flow field calculation method.The software can be used for design of compressor blades or improvement of existing blades.In this paper,design of two compressor blade profiles is taken as examples.The inlet Mach number of two cascades composed of the blades is about 0.5 and 0.9,respectively.To insure improvement of cascade aerodynamic performances in whole work ranges,the objective functions are constructed from consideration of both design and off design point performances.In the optimization procedure,three computers are run in parallel to reduce design time.The aerodynamic performances of optimal blades are obviously better than that of the initial blades.