Prediction of stall phenomenon in blade-to-blade passage of axial flow compressor

Abstract EN

The flow field between two blades was analyzed numerically by solving the steady, two dimensional and incompressible (time-mass averaged Navier- Stokes equations).

The (κ-ε) turbulent model was used to simulate the condition of the momentum equation and to obtain the eddy viscosity.

The SIMPLE algorithm is used to satisfy velocity-pressure coupling method and to satisfy the conservation of mass.

A computer code was constructed in this work using FORTRAN 90 language to simulate the flow.

The numerical results were compared with experimental results of other researcher for flow through the cascade of axial compressor, and were found to be in a good agreement.

Three different airfoils common, used for axial flow compressors blades, were investigated in the present study.

The study shows that stall happens.

At incidence angles (-80 to 70) for NACA 65(12)10 and (-9º to 3º) for NACA 65 (18) 10 and (-70 to 90) for NACA 65 (8) 10.

The result also show that stall happens when the total pressure loss is greater than 0.06 for NACA 65 (8) 10 when stagger angle is greater than 450 stall happens for total pressure loss less 0.06 as the outlet flow angle decreases.

However, the quasi-three dimensional, steady, incompressible, turbulent, adiabatic and single-phase fluid flow inside the blade-to-blade passage of an axial flow compressor stator was also studied and the study shows that Stall was seen to take place at blade tips during starting.