Design and Analysis of Stator, Rotor and Blades of the Axial Flow Compressor

Abstract

Axial flow compressor is one of the most important parts of Gas turbine. In design of Axial flow compressor the work presented comprises of basic flow parameters and dimensions of parts, this makes the further design process quite simple and the results will be helpful to take further changes or improvement at the time of detailed design. The objective of work presented is to design Axial flow compressor by using mean line method for a given mass flow rate and required pressure ratio. The parameters determined also include thermodynamic properties of the working fluid, stage efficiency, number of rotor and stator blades, tip and hub diameters, blade dimensions (chord, length and space) for both rotor and stator, Mach number, flow and blade angles (blade twist) . The same parameters are also determined for all five stages. The twist of the blades can be calculated along the blade length at any wrequired number of sections selected by the designers to obtain smooth blade twist profile. NACA 65410 profiles is used to generate coordinates of the blade. Further, in the process the first stage of axial flow compressor blade is developed using Solid works modeling. Also CFD simulation has been carried out using Ansys CFX to validate the results. Also Static structural Analysis has been performed to check whether the rotor is safe at given speed.