CFD analysis on the blades of an axial gas turbine

Abstract

This project analyzes two-dimensional linear cascade flows of an axial compressor on the stator vanes. It analyzes the influence of the angle of attack in the leading edge for different pressure ratios. The problem studied is a compressible, viscous and steady flow. A test case of an inviscid model flow has been carried out as well. Two types of grid are also being analyzed, the unstructured grid, with only triangular mesh elements, and a structured grid with only quadrilateral mesh elements. The modeling has been done with Gambit while the processing has been done with the Fluent code. To assure the validity of the results, this project is being compared with experimental results for two-dimensional experimental cascade performance for controlled diffusion compressor stator blading done by Sanger and Shreeve and with the work done by Jong-Uk Lee and Yun-ho Choi in the Numerical analysis of two-dimensional linear cascade flows paper.