Browse > Article

Reactive Fields Analysis of End-Burning Hybrid Combustor Using Tangential Oxidizer Injectors with Various Momentum Ratio  

Min, Moon-Ki (한국항공대학교 항공우주 및 기계공학과)
Kim, Soo-Jong (한국항공대학교 항공우주 및 기계공학부)
Kim, Jin-Kon (한국항공대학교 항공우주 및 기계공학부)
Moon, Hee-Jang (한국항공대학교 항공우주 및 기계공학부)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.11, no.2, 2007 , pp. 37-46 More about this Journal
Abstract
In this study, combustion fields of the end-burning hybrid combustor with tangential oxidizer injectors are examined. Momentum ratio of oxidizer is used as a main parameter to analyse the combustion efficiency with temperature, pressure, swirl velocity and mixture fraction field. It was found that as momentum ratio decreases the overall combustion efficiency is enhanced with the pressure field being insensitive to momentum ratio keeping quasi-uniform distribution. Irrespective to the momentum ratio, annular hot region commonly occurred in the upper combustion chamber where this phenomenon was left for a future improvement to be followed.
Keywords
End-burning Combustor; Hybrid Combustion; O/F Ratio; Momentum Ratio; Tangential Injector;
Citations & Related Records
연도 인용수 순위
  • Reference
1 S. J. Kim., J. K. Kim., S. C. Lee., W. J. You., J. P. Lee "A Study on Combustion Characteristics of Hybrid Rocket with the Variation of L/D Ratio", 2005 KSPE, pp, 31-38, 2005
2 M, A. Karabeyoglu., B, J Cantwell., D. Altman., "Development and Testing of Paraffin-Based Hybrid Rocket Fuels", 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 8-11, 2001, Salt Lake City, Utah
3 G. Marxman and M. Gilbert, "Turbulent Boundary Layer Combustion in the Hybrid Rocket", 9th Sym. Combustion, The Combustion inst. 1963.
4 S. J. Kim., J. K. Kim., J. Y. Koo., H. J. Moon., S. C. Cho., "The Study on Combustion Characteristic of End-burning Hybrid Rocket Engine", 2004 KSAS Spring Conference, 2004, pp. 625-628
5 Gary S. Haag, Martin N. Sweeting, and Guy Richardson "Low Cost Propulsion Development for Small Satellites at The Surrey Space Centre", 13th AIAA/USU Conference on Small Satellites. 1999
6 Gordon, S., and McBride, B.J. 1976. "Computer program for calculation of complex chemical equilibrium compositions, rocket performance, incident and reflected shocks, and Chapman-Jouguet detonations", NASA SP-273, Interim Revision, March
7 Dhir, V K., Chang, F., "Heat Transfer Enhancement Using Tangential Injector", ASHRAE TRANSACTIONS : Symposia, Vol.98, Pt.2, 1992, pp.383-390
8 S. C. Cho., S. J. Kim., S. C. Lee., J. K. Kim., J. Y. Koo., H. J. Moon., "Reactive Fields Analysis of Hybrid Combustor Under Different Arrangements of Oxidizer Injectors", 2005 KSPE, pp. 78-88
9 D. J. vonderwell, I. F. Murray, and S. D. Heister, "Optimization of Hybrid-Rocket- Booster Fuel-Grain Design", Journal of Spacecraft and Rockets, Vol. 32, No. 6, November-December 1995, pp. 964-969
10 Martin J. Chiaverini, "Regression Rate and Pyrolysis Behavior of HTPB-Based Solid Fuels In a Hybrid Rocket Motor", The Pennsylvania State University Ph.D. thesis, December 1997
11 W. S. Cha, "Thermo-Degradation Kinetics of Polyethylene", Vol. 10, No. 3, May 1999, pp. 432-437, J. Korean Ind. Eng. Chem
12 Brian Evans, Nicholas A. Favorito, and Kenneth K. Kuo, "Oxidizer-Type and Aluminum-Particle Addition Effects on Solid-Fuel Burning Behavior", AIAA paper 2006-4676, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 9-12, 2006, Sacramento, California
13 Star-CD Methodology Manual, Ver. 3.20, CD adapco Group, 2004
14 Risha, G. A., Boyer E., Wehrman R. B. and Kuo K. K., "Performance Comparison of HTPB-Based Solid Fuels Containing Nano-Sized Energetic Powder in a Cylindrical Hybrid Rocket Motor", 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 7-10, 2002, Indianapolis, Indiana
15 Estey, P. N., Altman, D., and McFarlane, J. S., "An Evaluation of Scaling Effects for Hybrid Rocket Motors", 1991, AIAA Paper 91-2520
16 Dianqi. F., Joseph. M., and Martin J. Chiaverini., "Hot Flow Model of the Vortex Cold Wall Liquid Rocket", AIAA paper 2004-3676, 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 11-14, 2004, Lauderdale, Florida
17 P. Markopoulos., T. Abel., "Development and Testing of a Hydrogen Peroxide Hybrid Upper Stage Propulsion System", 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 8-11, 2001, Salt Lake City, Utah
18 Marxman, G. A., Wooldridge, C. E., and Muzzy, R. J., "Fundamentals of Hybrid Boundary Layer Combustion", Progress in Astronautics and Aeronautics, Vol. 15, AIAA, New York, 1964, pp. 485-522