Abstract :
Turbojet engines are part of a gas turbine that are used to produce thrust
in aircraft. Along with the times, turbojet engines can still be optimized by
increasing the pressure ratio on the compressor (
) and the speed ratio of sound
to aircraft speed or commonly called the mach number (M) so that
thermodynamic analysis is needed on turbojet engines to determine whether the
engine can be optimized or not.
The thermodynamic analysis process carried out is calculating the
performance of the VIPER MK601 engine on IAR 99 aircraft with variations in
the increase in compressor pressure ratio (
) and mach number (M) during
cruising to obtain thrust specific (Fs) and specific fuel consumption (SFC) which
are calculated using excel to obtain the graph as a result of the engine
thermodynamic analysis and as a comparison to determine the optimal value of
the engine's performance..
The results of the performance calculation analysis showed that the
increase in the compression ratio Fs value increased until the value of (
)=10
then decreased after that point while the SFC value decreased. At an increase in
mach number, the Fs value has decreased while the SFC value has increased.