A gas turbine unit has a pressure ratio of 4,5:1. At the compressor inlet, the temperature is 16 C. Temperature increase across the combustion chamber is 395 C. Air flows through at a rate of 900 kg per minute. Assume that the working fluid throughout the unit has an adiabatic index and specific heat capacity of 1,4 and 1,005 kJ/kg.K respectively. Calculate: 6.1 6.2 6.3 6.4 6.5 The absolute outlet temperature of the compressor, combustion chamber, and turbine The network output of the unit in kilojoules per second The thermal efficiency of the unit Write a comment on the thermal efficiency of the unit as determined in QUESTION 6.3 Sketch a labelled temperature-entropy diagram and indicate any TWO temperature values on the diagram.