ANALISIS PERBANDINGAN PERFORMA ENGINE CFM56- 5A1 DENGAN V2500-A1 PESAWAT AIRBUS A320-200 PADA KONDISI CRUISING

DWI PRASETYO, ALRINO (2018) ANALISIS PERBANDINGAN PERFORMA ENGINE CFM56- 5A1 DENGAN V2500-A1 PESAWAT AIRBUS A320-200 PADA KONDISI CRUISING. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

The proverb says that "necessity is the trigger of an invention" in English is known as "necessity is the mother of invention". Based on this, aircraft engine manufacturing companies, namely CFMI and IAE, are competing to create the right engine for aircraft operational needs. One of CMFI and IAE's consumers is the French aircraft manufacturer, Airbus, which uses CFMI's CFM56-5A1 and IAE's V2500-A1 for the A320-200 aircraft. Because there are different engine variant options for the Airbus A320-200 aircraft, of course airlines as operators have considerations in using one of the engine products for their aircraft. The main factor that is considered is the performance of the engine. One way to determine engine performance can be done by using the parametric cycle analysis of real engines and engine performance analysis methods in cruising conditions, then analyzing the calculation results obtained with different height variation inputs, namely 24,000 ft, 24,000 ft, 32,000 ft and 36,000 ft. The best calculation results for the CFM56-5A1 and V2500-A1 engine performance are maximum cruise flight at an altitude of 36,000 feet, which has a thrust of 8,975 lbf and 8,341 lbf, TSFC of 0.6763 lbm/hr/lbf and 0.6818 lbm/hr/lbf, thermal efficiency of 53.2% and 50.5%, propulsive efficiency of 54.1% and 54.1% and overall efficiency of 28.8% and 28.6%. From the results of the performance comparison, the CFM56-A1 engine is superior in terms of thrust value, fuel consumption, thermal efficiency and overall efficiency while the V2500-A1 engine has the advantage of a higher propulsive efficiency value than the CFM56-5A1 engine. The effect of flight altitude on engine performance is that the higher the cruising flight, the thrust value, thrust specific fuel consumption and propulsive efficiency decrease while the thermal efficiency value and overall efficiency increase.

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