Air enters the diffuser of a turbojet engine with a mass flow rate of 39 kg/s at 62 kPa, 233 K, and a velocity of 225 m/s. The pressure ratio for the
compressor is 12, and its isentropic efficiency is 88%. Air enters the turbine at
1333 K with the same pressure as at the exit of the compressor. Air exits the
nozzle and turbine have isentropic efficiencies of 92% and 90%, respectively.
On the basis of an air-standard analysis, calculate
(a) the rate of heat addition, in kJ/h.
(b) the pressure at the turbine exit, in kPa.
(c) the compressor power input, in kJ/h.
(d) the velocity at the nozzle exit, in m/s.
(e) the thrust provided by the engine.