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On-design exergy analysis of a combustor for a turbojet engine: a parametric study

Ahmet Topal (TUSAS Engine Industries (TEI), Eskisehir, Turkey)
Onder Turan (Faculty of Aeronautics and Astronautics, Anadolu University, Eskisehir, Turkey)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 4 September 2017

215

Abstract

Purpose

The purpose of this study is to perform an exergy analysis of a turbojet engine combustor at different cycle parameters.

Design/methodology/approach

Base cycle parameters have been defined for the engine, and then differentiation of the combustor exergy efficiencies and destruction rates have been evaluated by changing overall pressure ratio, combustor exit temperature and combustor pressure ratio.

Findings

For the basic engine cycle, combustor unit is found to have lowest exergy efficiency as 62.3 for the sea level static condition. Compressor turbine exhaust and whole engine exergy efficiencies have been calculated as 88.7, 96.5, 68.2 and 69.4, respectively.

Practical implications

Because of the biggest exergy, destruction is seen mainly in combustion system; effect of the combustor inlet pressure (related to the compressor design technology), pressure drop and exit temperature on the exergy efficiencies have been analyzed and combustor second law efficiency have been evaluated.

Social implications

The investigation’s purposes are highly connected with social wellness and targeted at sustainable development of the society. Practical implementation of the obtained scientific results is directed on the improving of combustor for a turbojet engines and decreasing negative influence on the environment.

Originality/value

As a result of this paper, the following are the contribution of this paper in the field of gas turbine exergy subjects: Combustor has been found as the most critical component in respect of the exergy efficiency. Therefore, the effect of the combustor main cycle parameters such as inlet pressure, combustor pressure ratio and exit temperature have been analyzed.

Keywords

Citation

Topal, A. and Turan, O. (2017), "On-design exergy analysis of a combustor for a turbojet engine: a parametric study", Aircraft Engineering and Aerospace Technology, Vol. 89 No. 5, pp. 719-724. https://doi.org/10.1108/AEAT-12-2016-0254

Publisher

:

Emerald Publishing Limited

Copyright © 2017, Emerald Publishing Limited

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