한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제50권11호
  • /
  • Pages.783-789
  • /
  • 2022
  • /
  • 1225-1348(pISSN)
  • /
  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
권호 표지
DOI QR코드

DOI QR Code

하이브리드 로켓의 열음향 불안정과 연소압력 맥놀이 발생 모델링

Modeling for Thermoacoustic Instability and Beating Pressure Amplification in Hybrid Rocket Combustion

  • Hyun, Wonjeong (Department of Aerospace Engineering, Konkuk University) ;
  • Lee, Changjin (Department of Aerospace Engineering, Konkuk University)
  • 투고 : 2022.06.17
  • 심사 : 2022.09.27
  • 발행 : 2022.11.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

최근 연구에 의하면 하이브리드 로켓의 후연소실로 유입되는 연소유동은 고주파수 와류흘림을 포함하고 있으며, 노즐 벽면과 충돌하여 대향류가 형성되며 점화지연을 동반한 추가적인 연소가 발생하는 것이 확인되었다. 본 연구는 대향류 발생에 의한 점화지연이 연소압력 맥놀이가 나타나는 원인임을 확인하려 한다. 이를 위하여 Culick이 제안한 기존의 열음향 불안정 발생에 대한 에너지 킥 모델에 점화지연 발생을 반영한 수정 모델을 제안하였고 수치계산을 통하여 점화지연의 크기 변화가 열음향 결합에 의한 연소압력 맥놀이 발생을 결정하는 중요한 인자임을 확인하였다. 또한 후연소실 길이가 증가함에 따라 실험에서 관찰된 점화지연 감소는 에너지 킥과 압력의 위상 차의 증가를 가져와 맥놀이현상인 주기적인 압력증폭이 전혀 나타나지 않는 것도 확인하였다.

In a recent study, it was observed that the combustion gas entering the post chamber of a hybrid rocket contains vortices with very small size and high frequency characteristics. In addition, it was observed that small vortices collided with the nozzle wall to create a counter-flow, resulting in additional combustion with ignition delay. This study investigated the physical relationship between ignition delay induced by the counter-flow and the formation of beating pressure. To do this, a newly modified model was proposed by including ignition delay in the existing energy kicked oscillator model proposed by Culick. Numerical results show that the ignition delay is an important factor in determining the occurrence of the combustion pressure beats through the periodic formation of thermoacoustic coupling. In addition, when the ignition delay was reduced by increasing the post chamber length, the phase difference between the energy kick and the pressure generation was increased, the periodic pressure beats did not occur at all.

키워드

과제정보

본 연구는 한국연구재단의 기본연구사업(NRF-2021R1F1A10615161220682073250102)의 지원으로 수행한 연구결과이며, 일부는 2022학년도 건국대학교 연구년 교원 지원에 의해 수행되었습니다.

참고문헌

  1. Karabeyoglu, A., Zilwa, S. D., Cantwell, B. and Zilliac, G., "Modeling of hybrid rocket low frequency instabilities," Journal of Propulsion and Power, Vol. 21, No. 6, 2005, pp. 1107~1116. https://doi.org/10.2514/1.7792
  2. Hyun, W. J., Kim, J. A., Chae, H. S. and Lee, C. J., "Passive Control of Low-Frequency Instability in Hybrid Rocket Combustion," Aerospace, Vol. 8, No. 8, 2021, p. 204. https://doi.org/10.3390/aerospace8080204
  3. Messineo, J., Lestrade, J. Y., Hijlkema, J. and Anthoine, J., "Vortex shedding influence on hybrid rocket pressure oscillations and combustion efficiency," Journal of Propulsion and Power, Vol. 32, No. 6, 2016, pp. 1386~1394. https://doi.org/10.2514/1.B36049
  4. Kim, D. Y. and Lee, C. J., "Destabilization of the Shear Layer in the Post chamber of a Hybrid Rocket," Journal of Mechanical Science and Technology, Vol. 30, No. 4, 2016, pp. 1671~1679. https://doi.org/10.1007/s12206-016-0323-2
  5. Moon, Y. J. and Lee, C. J., "Dynamics of Post Chamber Flame and Combustion Pressure in Hybrid Rocket," 52nd AIAA Joint Propulsion Conference, July 2016, AIAA Paper 2016-4869.
  6. Kim, J. A. and Lee, C. J., "Low frequency instability and oscillating boundary later in hybrid rocket combustion," Journal of Mechanical Science and Technology, Vol. 34, No. 11, 2020, pp. 4831~4839. https://doi.org/10.1007/s12206-020-1039-x
  7. Hyun, W. J. and Lee, C. J., "Vortex shedding and Thermoacoustic instability in hybrid rocket combustion," 33rd international symposium and space technology and science, March 2022.
  8. Matveev, K. I. and Culick, F. E. C., "A model for combustion instability involving vortex shedding," Combustion Science and Technology, Vol. 175, No. 6, 2010, pp. 1059~1083. https://doi.org/10.1080/00102200302349
  9. Singaravelu, B. and Mariappan, S., "Stability analysis of thermoacoustic interactions in vortex shedding combustors using Poincare map," Journal of Fluid Mechanics, Vol. 801, 2016, pp. 597~622. https://doi.org/10.1017/jfm.2016.458
  10. Seshadri, A., Nair, V. and Sujith, R. I., "A reduced-order deterministic model describing an intermittency route to combustion instability," Combustion Theory and Modelling, Vol. 20, No. 3, 2016, pp. 441~456. https://doi.org/10.1080/13647830.2016.1143123
  11. Lee, S. H., Kim, D. Y. and Lee, C. J., "The frequency characteristics of the shear layer oscillation in hybrid rocket post-chamber," Aerospace Science and Technology, Vol. 70, 2017, pp. 388~395. https://doi.org/10.1016/j.ast.2017.08.007