Journal of the Korean Society of Combustion (한국연소학회지)

The Korean Society of Combustion (한국연소학회)
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Preliminary Design Program Development for Aircraft Gas Turbine Combustors : Part 1 - Combustor Sizing

항공용 가스터빈 연소기 기본 설계 프로그램 개발 : Part 1 - 연소기 크기 결정

  • 김대식 (강릉원주대학교 기계자동차공학부) ;
  • 유경원 (국방과학연구소 제4본부) ;
  • 황기영 (국방과학연구소 제4본부) ;
  • 민성기 (국방과학연구소 제4본부)
  • Received : 2013.07.13
  • Accepted : 2013.09.15
  • Published : 2013.09.30
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Abstract

This paper shows a general development process for aircraft gas turbine combustors. As a first step for developing the preliminary combustor design program, several combustor sizing methodologies using reference area concepts are reviewed. There are three ways to determine the reference area; 1) combustion efficiency approach, 2) pressure loss approach, 3) velocity assumption approach. The current study shows the comparisons of the calculated results of combustor reference values from the pressure loss and velocity assumption approaches. Further works are required to add iterative steps in the program using more reasonable values of pressure loss and velocities, and to evaluate the sizing results using data for actual combustor performance and sizes.

Keywords

References

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  1. Design Methodology of an Annular Combustor for Micro Gas Turbines vol.19, pp.4, 2014, https://doi.org/10.15231/jksc.2014.19.4.021
  2. Preliminary Design Program Development for Gas Turbine Combustor vol.20, pp.3, 2015, https://doi.org/10.15231/jksc.2015.20.3.027
  3. 연료의 미립화 및 증발 특성 데이터를 이용한 가스터빈 연소기 사이징 기법 고찰 vol.19, pp.3, 2013, https://doi.org/10.15435/jilasskr.2014.19.3.101