An Attempt to Predict the Performances of a Rocket Thrust Chamber
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.
[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.
[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.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:54200", author = "A. Benarous and D. Karmed and R. Haoui and A. Liazid", title = "An Attempt to Predict the Performances of a Rocket Thrust Chamber", 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.", volume = "6", number = "11", pages = "2390-6", }
