Abstract :
System simplest gas turbine consists of three components: a compressor, combustor
and turbine. The compressor is a mechanical device which serves to increase the pressure of
the fluid, ie air. The compressor is divided into two low pressure compressor and high
pressure compressore. In aircraft engines, compressors are used to increase the air pressure
that will be burned in the combustion chamber. Interest is increasing pressure to improve
combustion efficiency, because during the operation of aircraft that fly in cruising flight
altitude of the air temperature is very low so it is very difficult to do the burning. Therefore,
an increase or decrease in compressor pressure ratio will affect the engine performance
aircraft that is specific fuel consumption.
One way to determine the effect of compressor pressure ratio of the specific thrust
and specific fuel consumption can be achieved by parametric cycle analysis of real engine at
cruising conditions, then analyze the results of calculations obtained by the input variations
of different compressor pressure ratio.
The results of the performance calculation engine V2500-A1 at 28000 feet cruising
conditions showed specific thrustamounted to 18,664 lbf / (LBM / s), specific fuel
consumption ebesar 0.71 (LBM / h) / lbf, thermal efiiensi of 38,8%, 64,7% propulsive
efficiency, and the overall efficiency of 25,1%. From the results of the presure compressor
ratio to the engine performance is getting bigger compressor pressure ratio (?c) the specific
thrust will be greater, and the greater the compressor pressure ratio (?c), the specific fuel
consumption will be lower.