ANALISIS PENGARUH COMPRESSOR PRESSURE RATIO
TERHADAP SPECIFIC THRUST DAN SPECIFIC FUEL
CONSUMPTION ENGINE TURBOFAN GE90-85B
PADA KONDISI CRUISING
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
MUHAMAD ALWI TAMIMI, ILHAM
Subject
T Technology (General)
Datestamp
2024-04-05 03:24:16
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 GE90-85B at 35000 feet cruising conditions showed specific thrustamounted to 14,2011 lbf / (lbm/s), specific fuel consumption ebesar 0.5838 (lbm/ h) / lbf, thermal efiiensi of 38,3%, 76% propulsive efficiency, and the overall efficiency of 29,4%. The value of engine performance is known to decrease and increase with increasing and decreasing variation of the value of the parameter compressor pressure ratio. So that if the value of these parameters is greater, the fuel consumption when the aircraft operates will be less and the thrust will decrease. In addition to change the value of the output due to the influence of the compressor pressure value, variations in altitude are also very influential where the higher the aircraft, the resulting output value will be smaller.
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 GE90-85B at 35000 feet cruising conditions showed specific thrustamounted to 14,2011 lbf / (lbm/s), specific fuel consumption ebesar 0.5838 (lbm/ h) / lbf, thermal efiiensi of 38,3%, 76% propulsive efficiency, and the overall efficiency of 29,4%. The value of engine performance is known to decrease and increase with increasing and decreasing variation of the value of the parameter compressor pressure ratio. So that if the value of these parameters is greater, the fuel consumption when the aircraft operates will be less and the thrust will decrease. In addition to change the value of the output due to the influence of the compressor pressure value, variations in altitude are also very influential where the higher the aircraft, the resulting output value will be smaller.
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