Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지
DOI QR코드

DOI QR Code

Effect of Thermal Barrier Coating and Film Cooling Condition on the Cooling Performance of Liquid-propellant Rocket Engine Combustor

액체로켓 엔진 연소기의 열차폐 코팅 및 막냉각 조건에 따른 냉각 성능 변화 해석

  • Joh, Miok (Combustion Chamber Team, Korea Aerospace Research Institute) ;
  • Kim, Seong-Ku (Combustion Chamber Team, Korea Aerospace Research Institute) ;
  • Choi, Hwan-Seok (Combustion Chamber Team, Korea Aerospace Research Institute)
  • Received : 2013.07.07
  • Accepted : 2014.03.11
  • Published : 2014.04.01
Download PDF
⟨ Previous Next ⟩

Abstract

The effect of ceramic thermal barrier coating thickness on the cooling performance of a liquid-propellant rocket engine combustor has been investigated through combustion/cooling performance analysis whose results verified against measured data from hot-firing tests. Also have been confirmed the effects of film cooling amount near the face plate on the coolant temperature and on the thermal barrier coating surface temperature. Some important points to be considered for designing cooling schemes for regeneratively cooled rocket engine combustor have been drawn and reviewed from present study and further verification of the analysis tool should be performed in the future.

액체로켓 엔진 연소기에 대한 연소/냉각 성능 통합 해석 및 연소 시험 결과와의 비교를 통하여 내열 세라믹 열차폐 코팅 조건에 따른 냉각 성능 변화 경향을 고찰하였다. 연소기 헤드부 근처에서의 막냉각 적용 여부 및 막냉각 유량에 따른 냉각수 온도 및 열차폐 코팅 표면 온도 변화 경향 또한 확인하였다. 본 연구를 통하여 재생냉각 방식 로켓 엔진 연소기의 냉각 기구 설계 시 고려 사항이 검토되었으며, 향후 지속적인 해석 도구 검증이 수행될 예정이다.

Keywords

References

  1. Huzel, D.K. and Huang, D.H., Modern Engineering for Design of Liquid-Propellant Rocket Engines, American Institute of Aeronautics and Astronautics, Inc., 1992.
  2. Choi, H., Han, Y., Kim, Y. and Cho, G., "Development of 30-$Ton_f$ LOx/Kerosene Rocket Engine Combustion Devices(I)-Combustion Chamber," Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 37, No. 10, pp. 1027-1037, 2009. https://doi.org/10.5139/JKSAS.2009.37.10.1027
  3. Kim, J., Ahn, K., Joh, M. and Choi, H., "Conceptual Design of Thrust Chamber for 7 tonf-class Liquid Rocket Engine," Proceedings of the 2012 KSPE Spring Conference, pp. 454-456, May. 2012.
  4. Joh, M., Kim, S. and Choi, H., "A Trade-off Analysis between Combustion and Cooling Performance of a Liquid Rocket Combustor with Fuel Film Cooling Scheme," Journal of the Korean Society of Propulsion Engineers, Vol. 16, No. 6, pp. 16-22, 2012. https://doi.org/10.6108/KSPE.2012.16.6.016
  5. Naraghi, M.H., Dunn, S. and Coats, D., "A Model for Design and Analysis of Regeneratively Cooled Rocket Engines," 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Fort Lauderdale, FL, U.S.A., AIAA-2004-3852, Jul. 2004.
  6. Jokhakar, J. and Naraghi, M.H., "A CFD-RTE Model for Thermal Analysis of Regeneratively Cooled Rocket Engines," 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Hartford, CT, U.S.A., AIAA-2008-4557, Jul. 2008.
  7. Gorgen, J., Aichner, T. and Frey, M., "Spray Combustion and Heat Transfer Modeling in LOx/$H_2$, LOx/HC and MMH/NTO Combustion Chamber," 3rd European Conference for Aerospace Sciences, Versailles, France, Jul. 2009.
  8. Knab, O., Frey, M., Gorgen, J., Maeding, C., Quering, K. and Wiedmann, D., "Progress in Combustion and Heat Transfer Modeling in Rocket Thrust Chamber Applied Engineering," 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Denver, Co., U.S.A., AIAA-2009-5477, Aug. 2009.
  9. Kim, S., Joh, M. and Choi, H., "Film Cooling Modeling for Combustion and Heat Transfer within a Regeneratively Cooled Rocket Combustor," Proceedings of the 2011 KSPE Fall Conference, pp. 636-640, Nov. 2011.
  10. Kim, S., Han, S.H., Joh, M. and Choi, H., "Numerical Modeling of High-Pressure Combustion Processes of Kerosene/Liquid Oxygen within Liquid Rocket Combustion Chambers," Proceedings of the 2011 KSAS Fall Conference, Nov. 2011.
  11. Joh, M., Kim, S. and Choi, H., "Combustion/Cooling Performance Analysis of a Liquid Rocket Thrust Chamber with High Expansion Ratio," Proceedings of the 2012 KSPE Fall Conference, pp. 93-98, Nov. 2012.
  12. Park, T.S., Sung, H.J. and Suzuki, K., "Development of a Nonlinear Near-Wall Turbulence Model for Turbulent Flow and Heat Transfer," International Journal of Heat and Fluid Flow, Vol. 24, pp. 29-40, 2003. https://doi.org/10.1016/S0142-727X(02)00211-4
  13. Kim, S., Choi, H. and Kim, Y., "Thermodynamic Modeling based on a Generalized Cubic Equation of State for Kerosene/LOx Rocket Combustion," Combustion and Flame, Vol. 159, Issue 3, pp. 1351-1365, Mar. 2012. https://doi.org/10.1016/j.combustflame.2011.10.008
  14. Baek, K.H., private communication, Department of Nano Materials Engineering, College of Engineering at Chungnam National University.