Perform a cycle analysis for a turbojet engine at the following flight condition and corresponding
design parameters. Take the compressor and turbine efficiency to be 0.85 and 0.90 , respectively.
Table 1. Flight conditions.
Table 2. Engine Design Parameter.
a. Plot the T-S diagram illustrating the complete Brayton Cycle for this particular engine.
b. Plot the Total Pressure change at each station with respect to the station number.
1) Perform a cycle analysis for a turbojet engine at the following flight condition and corresponding design parameters. Take the compressor and turbine efficiency to be 0.85 and 0.90, respectively
Property Altitude Delta T from ISA Mach Number Burner Exit Temperature
Unit m K
Value 15000 0 1.5 1450
Comment
K
Table 1.Flight conditions.
Property Inlet Corr. Flow W2Rstd Intake Pressure Ratio Pressure Ratio Burner Exit Temperature Fuel Heating Value Overboard Bleed Burner Pressure Ratio
Unit kg/s
Value 32 0.99 12 1450 43.124 0 0.97
Comment
K MJ/kg kg/s
Table 2.Engine Design Parameter.
a. Plot the T-S diagram illustrating the complete Brayton Cycle for this particular engine
b.Plot the Total Pressure change at each station with respect to the station number