THERMAL SCIENCE

International Scientific Journal

EXERGETIC ANALYSIS OF AN AIRCRAFT TURBOJET ENGINE WITH AN AFTERBURNER

ABSTRACT
An exergy analysis is reported of a J85-GE-21 turbojet engine and its components for two altitudes: sea level and 11,000 meters. The turbojet engine with afterburning operates on the Brayton cycle and includes six main parts: diffuser, compressor, combustion chamber, turbine, afterburner and nozzle. Aircraft data are utilized in the analysis with simulation data. The highest component exergy efficiency at sea level is observed to be for the compressor, at 96.7%, followed by the nozzle and turbine with exergy efficiencies of 93.7 and 92.3%, respectively. At both considered heights, reducing of engine intake air speed leads to a reduction in the exergy efficiencies of all engine components and overall engine. The exergy efficiency of the turbojet engine is found to decrease by 0.45% for every 1°C increase in inlet air temperature.
KEYWORDS
PAPER SUBMITTED: 2011-09-11
PAPER REVISED: 2012-04-13
PAPER ACCEPTED: 2012-08-24
PUBLISHED ONLINE: 2013-05-05
DOI REFERENCE: https://doi.org/10.2298/TSCI110911043E
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2013, VOLUME 17, ISSUE 4, PAGES [1181 - 1194]
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© 2019 Society of Thermal Engineers of Serbia. Published by the Vinča Institute of Nuclear Sciences, Belgrade, Serbia. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution-NonCommercial-NoDerivs 4.0 International licence