Analysis of Single Stage Axial Flow Compressor by Varying the Axial Gap

axial flow compressors, spacing between the rotor and stator is an important parameter and plays a vital role in the performance characteristics. This parameter determines the compressor pressure ratio of the corresponding compressor. A study has been carried out to verify and explain the effect of axial spacing on the performance of 6.52 pressure ratio multi stage transonic compressor stage through CFD analysis using ANSYS FLUENT. Standard k-ε realizable turbulence model with standard wall function is used for analysis. Reynolds Averaged Navier-Stokes equations are discretized with finite volume approximations using hybrid grids. First the analysis was carried out for 31.5mm increase in axial gap and further the same amount was reduced and best operating conditions showed for the axial spacing +/- between the rotor and the stator. CFD values which were obtained were compared with the numerical values and validated. CFD analysis was carried out. This study showed good agreement with increase in axial spacing between the rotor and stator which increased the performance at the same time reducing the losses in the axial flow compressor.