Abstract
Turbulent two-phase reacting flow in the chamber of LOX/RP-1 bipropellant liquid rocket engine is numerically investigated in this paper. The predicted pressure and mean axial velocity are qualitatively consistent with the experimental measurements. The self-excited pressure oscillations are obtained without any disturbance introduced through the initial and boundary conditions. It is found that amount of abrupt pressure peaks appear frequently and stochastically in the head regions of the chamber, which are the important sources to drive and strengthen combustion instability. Such abrupt pressures are induced by local constant volume combustion, because local combustible gas mixtures with high temperature are formed and burnt out suddenly due to some fuel droplets reaching their critical state in a rich oxygen surrounding. A third Damköhler number is defined as the ratio of the characteristic time of a chemical reaction to the characteristic time of a pressure wave expansion to measure the relative intensity of acoustic propagation and combustion process in thrusters. The analysis of the third Damköhler number distributions in the whole thrust chamber shows that local constant volume combustion happens in the head regions, while constant pressure combustion presents in the downstream regions. It is found that the combustion instability occurs in the head regions within about 30 mm from the thruster head.
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Habiballah M, Lourme D, Pit F. PHEDRE-Numerical model for combustion stability studies applied to the Ariane Viking engine. J Propul Power, 1991, 7(3): 322–329
Habiballah M, Dubois I. Numerical analysis of engine instability. In: Yang V, Anderson W, eds. Liquid Rocket Engine Combustion Instability, Progress in Astronautics and Aeronautics, NASA. Washington D C: American Institute of Aeronautics and Astronautics, 1995, 169: 475–502
Hulka J, Hutt J J. Instability phenomena in a liquid oxygen/hydrogen propellant rocket engines. In: Yang V, Anderson W, eds. Liquid Rocket Engine Combustion Instability, Progress in Astronautics and Aeronautics, NASA. Washington D C: American Institute of Aeronautics and Astronautics, 1995, 169: 39–72
Lambiris S, Combs L P, Levine R S. Stable combustion processes in liquid propellant rocket engines. In: Combustion and Propulsion Fifth AGARD Colloquium. Braunschweig, 1962
Strahle W C. Unsteady laminar jet flame at large frequencies of oscillation. AIAA J, 1965, 3(5): 957–960
Abramzon B, Sirignano W A. Droplet vaporization model for spray combustion calculations. Int J Heat Mass Tran, 1989, 32(9): 1605–1618
Sirignano W A, Delplanque J P, Chiang C H, et al. Liquid-propellant droplet vaporization: A rate-controlling process for combustion instability. In: Yang V, Anderson W, eds. Liquid Rocket Engine Combustion Instability, Progress in Astronautics and Aeronautics, NASA. Washington D C: American Institute of Aeronautics and Astronautics, 1995, 169: 307–344
Hsiao G C, Meng H, Yang V. Pressure-coupled vaporization response of n-pentane fuel droplet at subcritical and supercritical conditions. P Combust Inst, 2011, 33(2): 1997–2003
Xu S L, Archer R D, Milton B E, et al. Unsteady transverse injection of kerosene into a supersonic flow. Sci China Ser E-Tech Sci, 2000, 43(2): 206–214
Chen J H, Zhang H Q, Li Z Y, et al. Investigation on extremal and critical characteristics of ignition time for H2/O2 combustion system and their applications. Sci China Ser E-Tech Sci, 2009, 52(5): 1161–1166
Gao Z X, Lee C H. A numerical study of turbulent combustion characteristics in a combustion chamber of a scramjet engine. Sci China Tech Sci, 2010, 53(8): 2111–2121
Tong A Y, Sirignano W A. Oscillation vaporization of fuel droplets in an unstable combustor. J Propul Power, 1989, 5(3): 257–261
Duvvur A, Chiang C H, Sirignano W A. Oscillatory fuel droplet vaporization-driving mechanism for combustion instability. J Propul Power, 1996, 12(2): 358–365
W. A. Sirignano, Wu G. Multicomponent-liquid-fuel vaporization with complex configuration. Int J Heat Mass Tran, 2008, 51(19–20): 4759–4774
Lei S, Turan A. Chaotic modeling and control of combustion instability due to vaporization. Int J Heat Mass Tran, 2010, 53(21): 4482–4494
Huang Y H, Wang Z G. Global model of liquid rocket engine combustion instability based on chemistry dynamics. In: 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, Indiana, AIAA, 2002. 2000–3992
Matalon M. Flame dynamics. P Combust Inst, 2009, 32(1): 57–82
Metzener P, Matalon M. Diffusive-thermal instabilities of diffusion flames: onset of cells and oscillations. Combust Theor Model, 2006, 10(4): 701–725
Law C K. Combustion Physics. New York: Cambridge University Press, 2006
James A, Maciej Z, Giridharan M G. Simulation of spray combustion instabilities in liquid rocket engines.II-Application. In: 35th AIAA/ASME/SAE/ASEE Aerospace Sciences Meeting and Exhibit, Reno, AIAA, 1997. 1997–0695
O’Rourke P J. The turn function and vorticity method for numerical fluid dynamics. J Comput Phys. 1985, 53(3): 361–376
Robin E, Schallenmuller A R, Lowhead R B. Displacement and shattering of propellant drops. United States Air Force of Scientific Research, 1960, TF 60–75
Ranz W E, Marshall W R. Evaporation from drops. I. Chem Eng Prog, 1952, 48(3): 141–146
Crowe C T, Sharma M P, Stock D E. The Particle-Source-In Cell (PSI-CELL) model for gas-droplet flows. J Fluids Eng, 1977, 99(2): 325–332
Libby P A, Williams F A. Turbulent Reacting Flows. German: Springer-Verlag, 1980
Strange G. On the construction and composition of difference schemes. SIAM J Numer Anal, 1968, 5(3): 506–517
Pindera M Z, Giridharan M G. Numerical studies of acoustic interactions with spray combustion. In: 32nd AIAA/ASME/SAE/ASEE Aerospace Sciences Meeting and Exhibit, Reno, AIAA, 1994. 1994–0685
Lambiris S, Combs L P. Steady-state combustion measurements in a LOX/RP-1 rocket chamber and related spray burning analysis. In: Penner S S, Williams F A, eds. Detonation and Two-Phase Flow. New York: Academic Press, 1962
Levine R S. Experimental status of high frequency liquid rocket combustion instability. Symposium (International) on Combustion, 1965, 10(1): 1083–1099
Harrje D T, Reardon F H. Liquid Propellant Rocket Combustion Instability. Washington D C: Scientific and Technical Information Office, NASA SP-194, 1972
Burstein S A, Chinitz W, Schechter H S. A nonlinear model of combustion instability in liquid propellant rocket engine. In: 8th Joint Propulsion Specialist Conference, New Orleans, AIAA, 1972, 1972–1146
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Zhang, H., Ga, Y., Wang, B. et al. Analysis of combustion instability via constant volume combustion in a LOX/RP-1 bipropellant liquid rocket engine. Sci. China Technol. Sci. 55, 1066–1077 (2012). https://doi.org/10.1007/s11431-012-4743-7
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DOI: https://doi.org/10.1007/s11431-012-4743-7