Air at \(290 \mathrm{~K}\) flows into the compressor of a gas turbine engine. The temperature increases to \(1350 \mathrm{~K}\) when it flows into the turbine. The pressure ratio is 15 and power output is \(5 \mathrm{MW}\). Assume the whole process is isentropic, evaluate 1. Thermal efficiency.

2. Fuel consumption. The lower calorific value of the fuel, \(Q_{p}^{\prime}\), is \(44,000 \mathrm{~kJ} / \mathrm{kg}\).

3. Ratio of turbine work and compressor work.

Take heat capacity ratio, \(\kappa_{\mathrm{air}}=1.38 ; c_{p}=1.05 \mathrm{~kJ} / \mathrm{kgK}\).

\([0.526,0.114 \mathrm{~kg} / \mathrm{s}, 2.2]\)