This article presents a new and simple method for the prediction of the compressor performance maps based on the geometry and the design point data. The method accurately calculates the compressor performance map based on a comprehensive one-dimensional row-by-row analysis. Off-design efficiency is determined using a modified diffusion factor and an advanced loss calculation method that allows for the accurate prediction of the operational characteristics of the compressor in the post-stall regime. Three different compressor performance maps are generated for low, intermediate and high pressure stage groups using the geometry of the multistage compressor of a power generation gas turbine engine. The results are compared with the maps obtained from experiment.

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