Optimization of Aerodynamic Characteristic of Compressor Cascade by Genetic Algorithm Assisted by Modified Vortex Panel Method

Axial compressor cascade blade shape optimization has been carried outto obtain improved aerodynamic performance using genetic algorithm optimization technique assisted by modified vortex panel flow solver. Three set of compressor cascades with aspect ratio 4.16, 3.246 and 2.0 have been designed and fabricated with solid side walls for experimental investigations. Compressor cascade mounting system has been designed and fabricated for mounting the cascade on the wind tunnel. To ensure resonance free testing in the wind tunnel and avoid flutter problems, Finite element model of compressor cascade mounting system has been developed and modal analysis have been carried out to glean the natural frequencies of vibration. NACA 9410-83 aerofoil has been chosenas a baseline aerofoil for blade section profile with 45, 55 and 65 degrees stagger angles respectively for high, medium and low aspect ratio compressor cascades. The compressor cascades have been tested at 0.06, 0.07 and 0.08 low subsonic Mach number and 0 to 5 degrees angle of attack. Modified vortex panel method has been formulated and validated by experimental investigations. Substantial differences in aerodynamic performance have been investigated between the baseline aerofoil profiled compressor cascade and genetic algorithm optimized aerofoil profiled compressor cascade.