An ideal, basic, air standard gas turbine engine has a compressor inlet temperature of 288 K, a compressor efficiency of 87%, a gas generator turbine efficiency of 89%, and a power turbine efficiency of 89%. The compressor pressure ratio is 12.0. Assuming variable specific heats, a turbine inlet temperature 1400 K, a compressor inlet pressure 101.3 kPa, and that air enters the compressor, at the rate of 1 kg/s, calculate: a- the pressure and temperature leaving the gas generator turbine b- the net power, rate at which heat is added, and cycle thermal efficiency assuming no pressure drop during the addition process and that the pressure at the power turbine exit is 101.3 kPa. d- the net power, rate which heat is added, and cycle thermal efficiency if there is a 3% pressure drop in the combustion chamber and the power turbine exit pressure is 1% above the compressor inlet pressure