A repeating stage model has been developed aiming at the simplification of the required global aerodynamic boundary conditions for the simulation of the rear stages of multistage axial flow compressors. A circumferentially non-uniform mixing plane approach is used to exchange information between neighbouring blade rows. A pressure correction method with the standard k - e turbulence model is used for the solution of discretised governing equations. Two computational cases are analysed and compared with experimental data, one for the third stage of the Cranfield Low Speed Research Compressor (LSRC) by using the repeating stage model and the other for the complete four-stage of the same compressor by setting the global aerodynamic boundary conditions in a conventional way. Comparable results from the two predictions are in good agreement with the experimental data, proving that the repeating stage model is a very economical and accurate alternative to the very expensive complete multistage simulations where only the rear stages are of interest.
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