An Attempt to Predict the Performances of a Rocket Thrust Chamber

Authors: A. Benarous, D. Karmed, R. Haoui, A. Liazid

Abstract:

The process for predicting the ballistic properties of a liquid rocket engine is based on the quantitative estimation of idealized performance deviations. In this aim, an equilibrium chemistry procedure is firstly developed and implemented in a Fortran routine. The thermodynamic formulation allows for the calculation of the theoretical performances of a rocket thrust chamber. In a second step, a computational fluid dynamic analysis of the turbulent reactive flow within the chamber is performed using a finite volume approach. The obtained values for the “quasi-real" performances account for both turbulent mixing and chemistryturbulence coupling. In the present work, emphasis is made on the combustion efficiency performance for which deviation is mainly due to radial gradients of static temperature and mixture ratio. Numerical values of the characteristic velocity are successfully compared with results from an industry-used code. The results are also confronted with the experimental data of a laboratory-scale rocket engine.

Keywords: JANAF methodology, Liquid rocket engine, Mascotte test-rig, Theoretical performances.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1060429

References:

[1] P. Caisso, et al ., "A Liquid propulsion panorama," Acta Astronautica, vol. 65, pp.1723-1737, 2009.
[2] G. Cai, J. Fang, X. Xu, and M. Liu, "Performance prediction and optimization for liquid rocket engine nozzle," Aerospace Science and Technology, vol. 11, pp.155-162, 2007.
[3] S.S. Dunn, and D.E. Coats, "Nozzle performance predictions use the TDK-97 code," AIAA paper 97-2807, 1997.
[4] M. Habiballah, et al., "Experimental studies of high pressure cryogenic flames on the Mascotte facility," Combustion Science and Technology, vol. 178, pp.101-128, 2006.
[5] JANAF, "Rocket Engine Performance Prediction and Evaluation," CPIA 246, April 1975.
[6] Ansys-Fluent Software, Ver.6.2.16, Lebanon, NH, USA, 2005.
[7] D.Y. Peng, and D.B. Robinson, "A new two-constant equation of state," Industrial Engineering Chemistry and Fundamentals vol. 15, no.1, pp.59-63, 1976.
[8] B.F. Magnussen, and B.H. Hjertager, "On mathematical models of turbulent combustion with special emphasis on soot formation and combustion," In Proceedings 16th International Symposium on Combustion, The Combustion Institute, Pittsburg, Penn., 1976, pp. 719- 729.
[9] G.P. Sutton, Rocket Propulsion Elements: An Introduction to the Engineering of Rockets. London: Wiley Interscience Publishing, 1986, ch. 3.
[10] S. Gordon, and B.J. Mc Bride, "Computer program for calculation of complex chemical equilibrium compositions and applications," NASA Reference Publication, no.1311, Lewis Research Center, Cleveland, OH,1994.
[11] J.L. Thomas, and S. Zurbach, "Test case RCM3: supercritical spray combustion at 60 bars at Mascotte," in Proceeding of the 2nd International Workshop on Rocket Combustion Modeling, Lampoldhausen, Germany, 2001, pp.13-23.
[12] M.M. Poschner, and M. Pfitzner, "Real gas CFD simulation of supercritical H2-LOX combustion in the Mascotte single-injector combustor using a commercial CFD code," AIAA Paper, 2008-952 2008.
[13] A. Benarous, A. Liazid, and D. Karmed, "H2/O2 combustion under supercritical conditions," In Proceeding of the 3rd European Combustion Meeting, Creete, Greece, 2007, pp.156-161.
[14] V. Yang, "Modeling of supercritical vaporization, mixing and combustion processes in liquid- fueled propulsion systems," The Combustion Institute, vol. 28, pp. 925-942, 2000.
[15] S. Chapman, and T.G. Cowling, The Mathematical Theory of Nonuniform Gases. London: Cambrigde University Press, 1952, ch. 8.
[16] S. Takahashi, "Preparation of a generalized chart for the diffusion coefficients of gases at high pressures," Journal of Chemical Engineering in Japan, vol. 7, no.6, pp. 417-420, 1974.
[17] T.H. Chung, M. Ajlan, L.L. Lee, and K.E. Starling, "Generalized multiparameter correlation for non polar fluid transport properties," Industrial and Engineering Chemistry Research, vol. 27, no.4, pp.671- 679, 1988.
[18] K. G. Harstad, R.S. Miller, and J. Bellan, "Efficient high pressure state equations," AIChE Journal, vol. 43, no.6, pp. 1605-1610, 1997.
[19] B.E. Launder, and D.B. Spalding, "The numerical computation of turbulent flows," Computational Methods in Applied Mechanical Engineering, vol. 3, pp.269-289, 1974.
[20] S.B. Pope, "An explanation of the turbulent round-jet/plane-jet anomaly," AIAA Journal, vol. 16, no.3, pp. 279-281, 1978.
[21] T. Poinsot, and D. Veynante, Theoretical and Numerical Combustion, Philadelphia: R. T. Edwards Editions, 2005, ch. 3.
[22] V. Schmidt, et al. "Experimental investigation and modeling of the ignition transient of a coaxial H2/O2 injector," In Proceedings 5th International Symposium on Space Propulsion, Chattanooga, Tenn., 2003, pp. 8 - 36.
[23] D. Gaffie, et al., "Numerical investigation of supersonic reacting hydrogen jets in a hot air co-flow," AIAA Paper, 01-1864, 2001.