액체로켓엔진 안정성 예측을 위한 시험적 기법 연구

Experimental study of combustion stability assesment of injector

  • 이광진 (한국항공우주연구원 우주추진기관실 엔진그룹) ;
  • 서성현 (한국항공우주연구원 우주추진기관실 엔진그룹) ;
  • 문일윤 (한국항공우주연구원 우주추진기관실 엔진그룹) ;
  • 한영민 (한국항공우주연구원 우주추진기관실 엔진그룹) ;
  • 설우석 (한국항공우주연구원 우주추진기관실 엔진그룹) ;
  • 이수용 (한국항공우주연구원 우주추진기관실 엔진그룹)
  • 발행 : 2003.12.12

초록

The objective of the present study is to develop methodology for the assesment of combustion stability of liquid rocket injectors. To simulate actual combustion occurring inside of a thrust chamber, a full-scale injector has been employed in the study, which burns gaseous oxygen and mixture of methane and propane. The main idea of the experiment is that the mixing mechanism is considered as a dominant factor significantly affecting combustion instability in a full-scale thrust chamber. Single & multi split triplet injectors have been used with an open-end cylindrical combustion chamber. The characteristics revealed by excited dynamic pressures in gaseous combustion show degrees of relative acoustic damping depending on operating conditions. Upon test results, the direct comparison between various types of injectors can be realized for the selection of the best design among prospective injectors.

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