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

Topal A., TURAN Ö.

AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, vol.89, no.5, pp.719-724, 2017 (SCI-Expanded) identifier identifier

  • Publication Type: Article / Article
  • Volume: 89 Issue: 5
  • Publication Date: 2017
  • Doi Number: 10.1108/aeat-12-2016-0254
  • Journal Name: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY
  • Journal Indexes: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Page Numbers: pp.719-724
  • Keywords: Exergy, Gas turbine, Propulsion, Combustor, Turbojet, BYPASS TURBOFAN ENGINE, TURBINE POWER-PLANTS, TURBOPROP ENGINE, GENERATION, EFFICIENCY, ALGORITHM, ENERGY, AID
  • Anadolu University Affiliated: Yes

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.