The use of Navier-Stokes simulation in the daily design process of multistage compressor requires extremely large computer resources. A less expensive alternate is the development of parallel numerical simulation on a workstations cluster for parallel distributed supercomputer. An average-passage model was introduced to include the unsteady flow effects and wake blockage and to make all of the flow variables are continues at the interface planes. A parallel Navier-Stokes solver has been developed for multistage high pressure ratio compressor based on domain decomposition methodology. This multiblade row solver was applied to analyze the flow field of the first 3 stage blade rows of a 7 stage high pressure ratio compressor at the design point.
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