Integrated Preliminary Design and CFD-Based Optimization of an Axial Compressor Stage Using Excel and ANSYS

This study presents a comprehensive framework for the preliminary design and aerodynamic analysis of an axial compressor stage by integrating one-dimensional (۱D) mean-line methods with three-dimensional computational fluid dynamics (CFD). Initially, thermodynamic and fluid mechanics principles are applied within Microsoft Excel to calculate velocity components, blade angles, enthalpy rise, and estimate initial efficiency. Subsequently, blade geometries are generated using BladeGen, meshed with TurboGrid, and simulated in ANSYS CFX employing the SST k-ω turbulence model. The CFD analysis yields detailed insights into pressure distribution, velocity contours, flow vectors, and power coefficient. Following validation, geometric optimization is conducted by varying parameters such as blade stagger angle, thickness, and leading-edge curvature. Results indicate that this integrated approach effectively enhances aerodynamic performance while maintaining computational efficiency. The proposed methodology is adaptable for multi-stage compressor designs and offers a practical tool for early-stage turbomachinery development.

کلیدواژه ها:

Axial compressor ، mean-line design ، CFD analysis ، ANSYS CFX ، blade optimization ، SST k-ω model ، aerodynamic performance ، Excel-based design ، turbomachinery