International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
권호 표지
DOI QR코드

DOI QR Code

Effect of Mixture Ratio Variation near Chamber Wall in Liquid Rocket Engine

  • Han, Poong-Gyoo (Space Div. Technical Research Institute, Hyundai MOBIS) ;
  • Kim, Kyoung-Ho (Space Div. Technical Research Institute, Hyundai MOBIS)
  • Published : 2003.11.30
Download PDF
⟨ Previous Next ⟩

Abstract

An experimental research program is being undertaken to develop a regeneratively-cooled experimental thrust chamber of liquid rocket engine using liquefied natural gas and liquid oxygen as propellants. Prior to firing test using a regenerative cooling with liquefied natural gas in this program, several firing tests were conducted with water as a coolant. Experimental thrust chambers with a thrust of about 10tf were developed and their firing test facility was built up. Injector used in the thrust chamber was of shear-coaxial type appropriate for propellants of gas and liquid phase and cooling channels are of milled rectangular configuration. Periodical variation of the soot deposition and discoloration was observed through an eyes' inspection on the inner wall of a combustion chamber and a nozzle after each firing test, and an intuitive concept of the periodical variation of mixture ratio near the inner wall of a combustion chamber and a nozzle at once was brought about and analyzed quantitatively. Thermal heat flux to the coolant was calculated and modified with the periodical variation model of mixture ratio, and the increment of coolant temperature at cooling channels was compared with measured one.

Keywords

References

  1. Kalmykov, G. P., Lebedinsky, Y. V., "Some Aspects of Development of New-Generation Econornical Environmentally-Friendly Engines for Prornising Injection Systems," 47th Intemational Astronautical Congress, IAF-96-S.1.04, Oct., Beijing, China, 1996.
  2. Kalmykov, G. P., Mossolov, S. V., "Liquid Rocket Engines working on Oxygen+Methane for Space Transportation Systems of XXI Century (on the Results of Scientific and Experimental Studies)," 51th IAF, lAF-00-S.2.10, Brazil, 2000.
  3. Giovanetti, A. J., Spadaccini, L. J., and Szetela, E. J., "Deposit Formation and Heat Transfer Characteristics of Hydrocarbon Rocket Fuels," Journal of Spacecraft and Rocket, Vol. 22, No. 5, 1984, pp. 574-580
  4. Tamura, H., Ono, F., Kumakawa, A., and Yatsuyanagi, N, "LOX/Methane Staged Combustion Rocket Combustor Investigation," AIAA/SAE/ASME/ASEE 23rd Joint Propulsion Conference. AlAA-87-1856, San Diego, CA, Jun 29-Jul 2, 1987.
  5. Sugathan, N., Srinivasan, K., and Sriruvasa Murthy, S., "Experiments on Heat Transfer in a Cryogeruc Engine Thrust Chamber," Journal of Propulsion and Power, Vol. 9, No. 2, 1993, pp. 240-244. https://doi.org/10.2514/3.23615
  6. Dobrovolski, M.B., Liquid Rocket Engines, 1968.
  7. Kim, K.H., Kim, Y.S., and Woo., Y.C., "Heat Transfer Analysis ofLiquid Rocket Engines," Conference of KSASS, Spring, 1996.
  8. Chang, H.S., Han, P.G., Cho, Y.H., "Effect of Regenerative Cooling on LRE Performance," Conference of KSASS, Korea, Autumn 2002
  9. Chang, H.S., Han, P.G., "Study on Regenerative Cooling Characteristics for Liquid Rocket Engine using LNG as a Fuel," Conference of KSPE, Korea, April 2002.
  10. Han, P.G., "Prediction Program of Wall Temperature of LRE," Unpublished Intemal Report, MOBIS, 2002.
  11. Wrobel, J., R., "Some Effects of Gas Stratification on Chocked Nozzle Flows," J. Spacecraft, Vol. 2, No. 6, 1965.
  12. Gordon, S., McBride, B., J., "Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Application," NASA Ref. Pub. 1311, Jun., 1996
  13. Huzel, D. K., Huang, D. H., Modem Engineering for Design of Liquid Propellant Rocket Engine, NASA SP-125, 1971
  14. Robert, C., Hendricks, A.K., Peller, I.C., and Baron, A.K., "W ASP- A Flexible Fortran lV Computer Code for Calculating Water and Steam Properties," NASA TN D-7391 , Nov. 1973.
  15. Robert, C., Hendricks, A.K., Baron, A.K., and Peller, I.C., "GASP- A Computer Code for Calculating the Thermodynamic and Transport Properties for Ten Fluids: Parahydrogen, Helium, Neon, Methane, Nitrogen, Carbon Monoxide, Oxygen, Fluorine, Argon, and Carbon Dioxide," NASA TN D-7808, Feb. 1975.
  16. Choi, S.J., Cho, C.Y., "Evaluation of Properties for Alternative Materials,"Technical report consigned by Hyundai MOBIS, KIMM, 2000
  17. Naraghi, M. H., User Manual for RTE 2002, Jan, 2002
  18. Naraghi, M. H, Quentmeyer, R. J., and Mohr, D. H., "Effect of a Blocked Channel on the Wall Temperature of a Regeneratively Cooled Rocket Thrust Chamber," AlAA/SAE/ASME/ASEE 37th Joint Propulsion Conference, AlAA 2001-3406, Salt Lake City, Utah, July 8-11, 2001