(a) A gas turbine draws air at 300 K and 100 kPa at inlet, and operates at a pressure ratio of 12. The temperature at the exit of the combustion chamber is 1400 K. Assume that the compressor and the turbine have isentropic efficiencies of 0.85 and 0.85, respectively. Ignore any pressure drop between the compressor and the turbine. Assuming a y of 1.4 for the gas. Draw a T-s diagram of the gas turbine cycle and find the temperatures at compressor exit and turbine exit. State your assumptions. [15 marks]