Axial Flow Compressor Design for High Pressure Applications of Land and Jet-Based Engines

The objective of this project is to design and analyze an axial flow compressor that will enable jet and land-based engines to achieve high pressure ratios. Utilizing cutting-edge 3D design techniques, the compressor is modeled with optimal blade geometry to optimize aerodynamic performance. The study focuses on important performance metrics under various operating situations, including efficiency, mass flow rate, and pressure ratio. 3D printing is used to create a scaled prototype, which is then tested in a wind tunnel fitted with sensors to gauge velocity, pressure, and airflow patterns. The study emphasizes the significance of stage arrangement, blade design, and flow stability in attaining high-performance compression by mimicking real-world situations.