Abstract
An influence of the performance degradation of compressor on operating lines of turbo jet engine has been investigated. A model has been developed to estimate the deteriorated centrifugal compressor performance such as pressure ratio and adiabatic efficiency by increasing impeller surface roughness. The modified compressor performance map has been utilized to investigate the effect of performance degradation on running lines of turbo jet engine. The running lines on compressor map have been determined by the matching calculation of components such as compressor, turbine and propelling nozzle. It has been observed that the running lines on the compressor map have been shifted toward surge line, resulting in the loss of thrust and in rising turbine inlet temperatures by increasing blade surface roughness.
