Modélisation en 3D et analyse des écoulements internes dans le compresseur axial Nasa Stage 37 Via ANSYS CFX

Abstract

This study focuses on the modeling, simulation, and analysis of the aerodynamic behavior of a NASA Stage 37 transonic axial compressor using computational fluid dynamics (CFD) with the ANSYS Fluent software. This compressor is a widely used reference case in the field of turbomachinery for studying compressible flows and high-speed transonic phenomena. A three- dimensional numerical model was developed to solve the conservation equations for mass, momentum, and energy. The simulation incorporates appropriate physical models, including turbulence models, rotational effects, and rotor-stator interactions. Boundary conditions were defined to reproduce the actual operating conditions of the compressor. The main objective of this study is to evaluate the aerodynamic performance of the NASA Stage 37 through the analysis of key parameters such as the compression ratio, isentropic efficiency, pressure distribution, velocity fields, and internal aerodynamic losses. The results obtained also allow the study of complex phenomena present in transonic compressors, such as shock waves, flow separations, and recirculation zones. Finally, this numerical approach offers a better understanding of the compressor's hydrodynamic behavior and provides an important basis for optimizing performance and improving the design of modern turbomachinery.