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Exergy indicators of a low-emission aero-engine combustor

Yasin Şöhret (Department of Airframe and Powerplant Maintenance, Suleyman Demirel University, Isparta, Turkey)
T. Hikmet Karakoc (Faculty of Aeronautics and Astronautics, Anadolu University, Eskisehir, Turkey)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 5 March 2018



It is essential to develop more environment-friendly energy systems to prevent climate change and minimize environmental impact. Within this scope, many studies are performed on performance and environmental assessments of many types of energy systems. This paper, different from previous studies, aims to prove exergy performance of a low-emission combustor of an aero-engine.


It is a well-known fact that, with respect to previous exergy analysis, highest exergy destruction occurs in the combustor component of the engine. For this reason, it is required to evaluate a low-emission aero-engine combustor thermodynamically to understand the state of the art according to the authors’ best of knowledge. In this framework, combustor has been operated at numerous conditions (variable engine load) and evaluated.


As a conclusion of the study, the impact of emission reduction on performance improvement of the aero-engine combustors exergetically is presented. It is stated that exergy efficiency of the low-emission aero-engine combustor is found to be 64.69, 61.95 and 71.97 per cent under various operating conditions.

Practical implications

Results obtained in this paper may be beneficial for researchers who are interested in combustion and propulsion technology and thermal sciences.


Different from former studies, the impact of operating conditions on performance of a combustor is examined from the viewpoint of thermodynamics.



The authors would like to thank Suleyman Demirel and Anadolu Universities of Turkey for the provided support.


Şöhret, Y. and Karakoc, T.H. (2018), "Exergy indicators of a low-emission aero-engine combustor", Aircraft Engineering and Aerospace Technology, Vol. 90 No. 2, pp. 344-350.



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