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Development Status of Technology Demonstration Model for Staged Combustion Cycle Engine

다단연소사이클 엔진 기술검증시제 개발 현황

  • Kim, Chaehyoung (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Lee, Jungho (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Woo, Seongphil (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • So, Younseok (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Yi, SeungJae (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Lee, Kwang-Jin (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Cho, Namkyung (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Han, Yeoungmin (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Kim, Jin-han (Rocket Engine Development Office, Korea Aerospace Research Institute)
  • Received : 2018.12.26
  • Accepted : 2019.05.10
  • Published : 2019.08.01

Abstract

Staged combustion cycle engines exhibit higher combustion performance compared with open cycle engines with a gas generator. An advanced research of the staged combustion cycle engine is going on for the next program following the KSLV-II program. Various experiments have been carried out for the technology demonstration model, TDM0A and TDM0B. The experiments on the combustion performance are aimed to understand the engine start condition and combustion characteristics. They also aim to develop the oxidizer-rich pre-burner and the combustor of the staged combustion cycle engine. The engine-shaped model, TDM1A is fabricated based on the experimental data. The combustion experiment of the TDM1A shows that the combustion pressure of the combustor is approximately 91 bar and the turbine rotation is approximately 28,00 rpm. The result is stable and satisfies the development requirements. The present paper reports on the development process and characteristics of engine models from TDM0A to TDM1A.

다단연소사이클 엔진은 가스발생기 기반의 개방형 엔진에 비해 성능이 좋기 때문에 현재 한국형발사체사업(KSLV-II)의 후속사업의 일환으로 선행연구가 진행 중이다. 기술검증시제 명칭의 TDM0A, TDM0B를 통해 다단연소사이클 엔진의 시동 조건과 연소 특성을 이해하고, 산화제 과잉 예연소기와 연소기 개발을 위한 연소 성능 시험이 수행되었다. 시험 데이터를 토대로 엔진 형상 모델 TDM1A를 제작하여 연소 시험을 수행했으며, 주연소기 연소압 91 bar, 터보펌프 회전수 28,000 rpm의 안정적인 결과로 개발요구조건을 만족하였다. 본 논문에서는 TDM0A부터 TDM1A까지의 개발과정과 특징에 대해 논하고자 한다.

Keywords

References

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