The overall compression ratio in a gas turbine engine is 12/1 which is performed in threestages with pressure ratios of 2.5/1, 2.4/1, and 2/1 respectively. The air inlet temperatureto the plant is 25 °C and intercooling between stages reduces the temperature to 40 °C. TheHP turbine drives the HP and intermediate-pressure compressor stages; the LP turbinedrives the LP compressor and the generator. The gases leaving the LP turbine are passedthrough a heat exchanger which heats the air leaving the HP compressor. The temperature atthe inlet to the HP turbine is 650 °C, and reheating between turbine stages raises thetemperature to 650 °C. The gases leave the heat exchanger at a temperature of 200 °C. Theisentropic efficiency of each compressor stage is 0.83, and the isentropic efficiencies of theHP and LP turbines are 0.85 and 0.88 respectively. Take the mechanical efficiency of eachshaft as 98%. The air mass flow is m kg/s. Neglecting pressure losses and changes in kineticenergy, and taking the specific heat of the water as 4.19 kJ/kg K. For the compression processtake cp = 1.005 kJ/kg K and γ = 1.4; for the combustion process, and for the expansion processtake cp = 1.15 kJ/kg K and γ = 1.333. Neglect the mass of fuel.
(i) Compute the power output in kilowatts;
(ii) Calculate the cycle efficiency;
(iii) Calculate the flow of cooling water required for the intercoolers when the rise inwater temperature must not exceed 30 K;
iv) Calculate the heat exchanger thermal ratio.
Where;
m = (2 × Student Registration Number) kg/sec