A gas turbine utilizes two – stage centrifugal compressor. The pressure ratios for the first and second stages are 2.5 and 2.1 respectively. The flow of air is 10 kg/s, this air being drawn at 1.013 bar and 200 C. If the temperature drop in the intercooler is 600C and the isentropic efficiency is 90% for each stage, calculate:
(i) the actual temperature at the end of each stage and
(ii) The total compressor power.
Assume $\gamma$ = 1.4 and Cp = 1.005 kJ/kg K for