Exergetic analysis of an aircraft turbojet engine with an afterburner | Zendy

M.A. Ehyaei | Zendy; A. Anjiridezfuli | Zendy; Marc A. Rosen | Zendy

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Exergetic analysis of an aircraft turbojet engine with an afterburner

Author(s) -

M.A. Ehyaei,

A. Anjiridezfuli,

Marc A. Rosen

Publication year - 2013

Publication title -

thermal science

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.339

H-Index - 43

eISSN - 2334-7163

pISSN - 0354-9836

DOI - 10.2298/tsci110911043e

Subject(s) - turbojet , exergy , nozzle , gas compressor , environmental science , brayton cycle , turbine , automotive engineering , combustion chamber , marine engineering , jet engine , aerospace engineering , combustion , engineering , waste management , chemistry , organic chemistry

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

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