An aerothermodynamic model for a widely used industrial gas turbine engine compressor has been developed for studying in-situ compressor deterioration due to atmospheric fouling at high power settings. The model is developed using available geometrical dimensions of the compressor annulus. It is based on a mean line stage stacking method utilizing the basic turbomachinery equations. The model requires minimum inputs (mass flow, compressor speed, ambient conditions) from the instrument sensors and derives all the necessary information (compressor discharge temperature and pressure, isentropic efficiency, and power) that defines overall performance. The validity of the model was confirmed by comparing the results with the field tests and excellent agreement was achieved. The model is very economical in operation and is fully capable of detecting small changes that occur in the compressor due to fouling.

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