Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Development of a 30 kW Hydrogen-Fueled Micromix Combustor for Research

연구용 30 kW 수소 전소 마이크로믹스 연소기 개발

  • Seojun Ock (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Minsu Kim (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Suhyeon Park (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • 옥서준 (한국항공대학교, 항공우주및기계공학부) ;
  • 김민수 (한국항공대학교, 항공우주및기계공학부) ;
  • 박수현 (한국항공대학교, 항공우주및기계공학부)
  • Received : 2023.10.21
  • Accepted : 2023.11.15
  • Published : 2023.12.31
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Abstract

Hydrogen-fueled gas turbines are a promising technology that can resolve the carbon dioxide emission issue as future aviation propulsion engines and carbon-free power generations. To achieve high efficiency and stability of gas turbines using 100% hydrogen as fuel, an innovative design of combustor systems is necessary to consider the characteristics of hydrogen, which are different from those of conventional hydrocarbon fuels. Micromix is a combustor design method, which aims to terminate the reaction quickly by intense mixing of fuel and air, consequently reducing NOx and increasing the stability. In this paper, we examine the principles and design process of micromix combustors as a pure-hydrogen combustion technology, and we introduce a design of a 30 kW micromix hydrogen combustor for research.

수소 가스터빈은 미래 항공 추진 기관과 무탄소 발전 동력원으로 이산화탄소 배출 문제에 대응할 수 있는 유망한 기술이다. 100% 수소를 연료로 사용하는 가스터빈을 위해서는 기존 탄화수소 연료와 다른 수소의 특성을 고려하여 효율과 안정성이 높은 혁신적인 연소기 시스템을 설계할 필요가 있다. 마이크로믹스는 연료와 공기를 강하게 혼합하여 반응이 빠르게 종료되도록 함으로써 질소산화물을 저감하고 안정성을 높이도록 하는 연소기 설계 방식이다. 본 논문에서는 수소 전소 기술로서 마이크로믹스 방식 연소기의 원리와 설계 방법을 살펴보고, 연구용 30 kW 마이크로믹스 수소 연소기 설계안을 소개한다.

Keywords

Acknowledgement

이 논문은 2023년도 정부(교육부)의 재원으로 한국연구재단의 지원을 받아 수행된 기초연구사업임 (과제번호: 2022R1A6A1A03056784). 또한, 이 논문은 한국항공대학교 2023년 재단 기금 연구과제 연구비를 제공받아 수행되었음.

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