The effects of the Control of Combustion Instabilities in accordance with various Acoustic Cavities

음향공 형상에 따른 연소 불안정 제어 효과

  • 차정필 (충남대학교 항공우주공학과) ;
  • 양재준 (충남대학교 항공우주공학과) ;
  • 서주형 (충남대학교 항공우주공학과) ;
  • 김홍집 (한국항공우주연구원 엔진그룹) ;
  • 고영성 (충남대학교 항공우주공학과)
  • Published : 2006.05.01

Abstract

Acoustic cavity as a stabilization device to control high-frequency combustion instabilities in liquid rocket engine is adopted and its damping capacity is verified in atmospheric temperature. Geometric effects of acoustic cavity on damping characteristics are analyzed and compared quantitatively. Satisfactory agreements have been achieved with linear acoustic analysis and experimental approach. Results show that the acoustic cavity of the largest orifice area or the shortest orifice length was the most effective in acoustic damping of the harmful resonant frequency finally, it is proved that an optimal design process is indispensable for the effective control of combustion instabilities.