Structural and fluid flow analysis of subsonic aircraft jet engine centrifugal compressor

Centrifugal compressor plays a vital role in aircraft jet engine propulsive industry. All the mini gas turbine engines are effectively using centrifugal compressor. Comparatively with axial flow compressor, the centrifugal compressor have low cost with lower pressure ratios. Therefore it is very much essential and important to increase the performance of the centrifugal compressor for upcoming pure-jet engine propulsion system. Aircraft industry much focusing on type of materials selecting the centrifugal compressor and how well the component is stable aerodynamically. To achieve the best performance in centrifugal compressor this paper more focused on a systematic numerical simulation approach as it can complete in an easier way with less computational facility. The main focus given in this paper to improve the performance of the centrifugal compressor under different materials selection and different mass flow rates of air. A systematic literature review conducted on centrifugal compressor materials and its aerodynamic behavior. The work carried out under both the structural and flow simulations using ANSYS tool. Basic methodology involves the geometrical modelling using Cero parametric version 2.0 tool. The same model was imported into ANSYS tool to perform the meshing for flow simulations. The work further carried out the simulations by applying the suitable boundary conditions at a subsonic speed. To have the better reliability of numerical analysis results the compressor performed at different mass flow rates with suitable grid independence check. The numerical simulation work also attempted with different types of aluminum materials selection with varying mas flow rates. Finally the improved efficiency results also compared with the experimental data from the literature for better aero mechanical features.