Question

As a propulsion engineer, you are tasked with testing the turbojet engine of an aircraft to determine its performance characteristics.  The turbojet engine is analyzed on an air-standard basis based on the Brayton cycle. Air, with a velocity of 265 m/s and volumetric flow rate of 230 m³/s, enters the diffuser at 18 kPa, -57^oC, and exits at 30 kPa.  The compressor pressure ratio is 15 to 1. The maximum temperature exiting the combustor is 1087^oC. The pressure exiting the nozzle is 18 kPa. The compressor, turbine and nozzle have efficiencies of 87%, 89% and 97%, respectively. Applying air standard assumptions, determine:  

A. The schematic and T-s diagrams

B. The power input of the compressor

C. The velocity at the nozzle exit

D. The mass flow rate of air into the engine

E. The thrust developed by the engine

F. The propulsive efficiency of the engine

Answer 1