ANALISIS PENGARUH COMPRESSOR PRESSURE RATIO TERHADAP SPECIFIC FUEL CONSUMPTION ENGINE TURBOFAN V2500-A1 PESAWAT AIRBUS 320-200 PADA KONDISI CRUISING

RAHMADANIAH, R.A. (2019) ANALISIS PENGARUH COMPRESSOR PRESSURE RATIO TERHADAP SPECIFIC FUEL CONSUMPTION ENGINE TURBOFAN V2500-A1 PESAWAT AIRBUS 320-200 PADA KONDISI CRUISING. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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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 (πc) the specific thrust will be greater, and the greater the compressor pressure ratio (πc), the specific fuel consumption will be lower.

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