In the an ideal turbo jet, the engine is designed such that the turbine work is divided equally between the compressor and the propeller. The gas from the turbine discharges to a nozzle for additional thrust. Consider such an engine where the air enters the diffuser at 200 m/s, 40 kPa, 240 K, and a flow rate of 40 kg/s. The compressor ratio is 11, and the turbine inlet temperature is 1200 K. The fuel used as a heating value of 43,000 kj/kg.
The solution is provided equationally in attachments.