Browse > Article
http://dx.doi.org/10.6108/KSPE.2013.17.4.081

Design Point Operating Characteristics of an Oxidizer Rich Preburner  

Moon, Ilyoon (Advanced Rocket Research Team, Korea Aerospace Research Institute)
Moon, Insang (Advanced Rocket Research Team, Korea Aerospace Research Institute)
Kang, Sang Hun (Advanced Rocket Research Team, Korea Aerospace Research Institute)
Ha, Seong-Up (Advanced Rocket Research Team, Korea Aerospace Research Institute)
Lee, Soo Young (Advanced Rocket Research Team, Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.17, no.4, 2013 , pp. 81-88 More about this Journal
Abstract
It was designed and tested at the design point that an oxidizer rich preburner for a staged combustion liquid rocket engine propelled by kerosene and LOx. The oxidizer rich preburner was designed as some of LOx injected from the mixing head was burned with kerosene and the rest of LOx injected from injection holes in the regenerative cooling chamber was vaporized by combustion gas. The preburner is operated at OF ratio of 60 and combustion pressure of 20 MPa. The Preburner has a honey-comb type mixing head with simplex swirl injectors, a turbulence ring improving combustion stability and uniformity of product gas temperature distribution, and a nozzle simulating the duct. With the combustion test results at the design point, the oxidizer rich preburner showed high combustion stability and uniformity of product gas temperature distribution.
Keywords
Liquid Rocket Engine; Staged Combustion; Preburner; Oxidizer Rich; Combustion Test;
Citations & Related Records
연도 인용수 순위
  • Reference
1 Katorgin, B.I., Chvanov, V.K., Chelkis, F.J., Irina G. Lozino-Lozinskaya, I.G. and Tanner, L.G., "Oxidizer-Rich Staged Combustion Rocket Engines Use and Development in Russia," AIAA Space Programs and Technlogies Coference, 1995.
2 Ha, S.U., Yoo, J.H., Moon, I.Y. and Moon, I.S., "Development History and Modern Trends of Oxidizer-Rich Prebrner," Proceedings of the 2012 Korean Society of Propulsion Engineers Spring Conference, pp. 461-464, 2012.
3 Ha, S.U., Lee, S.M., Kang, S.H. and Lee, S.Y., "Numerical Analysis on the Supercritical Combustion in Oxidizer-Rich Preburner with Triplex Injector," Proceedings of the 2012 Korean Society of Propulsion Engineers Fall Conference, pp. 490-493, 2012.
4 Yi, Y.S., Hong, M.G. and Lee, S.Y., "Study on the Spray Pattern of a Gas-centered Swirl Coaxial Injector with Various Injection Conditions," The 16th Annual Conference on Liquid Atomization and Spray Systems, pp. 64-65, 2012.
5 Moon, I.Y., Moon, I.S., Yoo, J.H., Jeon, J.H., Lee, S.M., Hong, M.G., Ha, S.U., Kang, S.H. and Lee, S.Y., "Ignition Test of an Oxidizer Rich Preburner," Proceedings of the 2011 Korean Society of Propulsion Engineers Fall Conference, pp. 869-872, 2011.   과학기술학회마을
6 Moon, I.Y., Moon, I.S. and Lee. S.M., "Study on the Product Gas Temperature Uniformity from a Mixing Head of an Oxidizer Rich Preburner," Proceedings of the 7th National Congress on Fluids Engineering, pp. 455-456, 2012.
7 Kim, Y.J., Hong, M.G., Lee, S.Y. and Sohn, C.H., "A Numerical Study on Mixing Characteristics for Recess Length of Swirl Coaxial Injector," Proceedings of the 2011 Korean Society of Propulsion Engineers Fall Conference, pp. 74-77, 2011.   과학기술학회마을
8 Huzel, D.K. and Huang, D.H., "Modern Engineering for Design of Liquid-propellant Rocket Engines," AIAA, 1992.
9 Parsley, R.C., Zhang, B., "Thermodynamic Power Cycles for Pump-Fed Liquid Rocket Engines," Liquid Rocket Thrust Chambers: Aspects of Modeling, Analysis, and Design, Progress in Astronautics and Aeronautics, Vol. 200, AIAA, Chap. 18, 2004.
10 Farhangi, S., Jensen, R.J., Hunt, K., Tuegel, L. and Yu, T., "Oxidizer-Rich Preburner Technology for Oxygen/Hydrogen Full Flow Cycle Applications," Progress in Astronautics and Aeronautics, Vol. 200, 2004.
11 Knuth, W.K. and Crawford, R.C., "Oxygen-Rich Combustion Process Applications and Benefits," Modern Engineering for Design of Liquid-propellant Rocket Engines", AIAA, 1992.