Table 2:

Engine Speed = 101500RPM

Turbine outlet temp (T4)= 600 degrees c

Fuel consumption rate = 9.31s/100ml

In the turbojet lab, a model aircraft engine operates on a pure turbojet cycle as illustrated in Fig. 1. The turbojet does not have a diffuser. The pressure ratio of the compressor, P/P, is a function of the engine. speed, 2, as expressed as P/P=2.76x10-102-9x102+1.37 Table 1 lists the test conditions and air and fuel properties. Use the data collected in Table 2 and answer the following questions. Compressor C FIL 2 T P qfuel Pfuel 0.81 kg/L Cp, air 1.00 kJ/kg/K 100 Turbine 3 4 Combustion Shaft chamber Nozzle Figure 1: schematic of the turbojet engine PR Table 1 Test conditions and properties of working fluids 25C Ambient temperature 1 bar Ambient pressure 43,000 kJ/kg fuel Lower heating value of fuel (kerosene) Density of fuel (kerosene) Constant pressure specific heat of air