Computational Analysis of Compressor Blade
This computational work aims at analyzing the flow behavior through a linear cascade of compressor blades with the help of Computational Fluid Dynamics using the FLUENT software. An attempt has been made to study the boundary layer behavior on the blades at various flow incidence angles and Reynolds numbers, based on flow inlet velocity and blade chord. A Computational Fluid Dynamics based computational model is created with the reference to an experimental work already carried out. This study will bring out the methodology for solving the problem using Computational Fluid Dynamics tools. Particularly, the capability of turbulence model to predict laminar, turbulent and transition in the boundary layer flows has been made. The geometric modeling and meshing of the flow domain has been carried out using the software’s CATIA and GAMBIT respectively.Development of boundary layer, point of flow separation, flow reattachment and pressure coefficient over the blade surfaces have been found and compared with the experimental results.