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u00a0P.K. Dash, Siddalingappa P.K, Lavanya S.,
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nJanuary 9, 2023 at 11:16 am
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nAbstract
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Combustion instability is a major problem in most solid rocket motor (SRM) during its operation. More form of instability is generated due to several factors like coupling of combustion acoustic waves with flow dynamics, grain configuration, combustion chamber design, combustible mixture, etc. This type of flow turbulence is sustained in such system for long durations and leads to failure of the mission. In this paper, an effort has been made to understand the vortex shading inside the rocket motor through cold flow analysis. A computational model is designed and run in a platform of fluid flow analysis software FLUENT. The vortex generated at the dead end of combustion chamber has been determined under laminar and turbulent flow conditions. A scaletoscale model of Shanbhogue’ experimental setup has been developed and grid to two different number of cells, i.e., 40000 and 60000 respectively. Comparison of computational and experimental results and influence of number of cells on computational results have been determined in present investigation. The effect of perturbation in an unsymmetric fluid flow is estimated and sizable changes are noted on the pressure waves at vortex point with respect to flow behavior i.e., laminar and turbulent. All results are presented in form of table and graphs.
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Keywords Combustion instability, laminar, SRM, turbulent, vortex shedding
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References
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1. Elias I, Gordon R. Vibration of gas at ambient pressure in a rocket thrust chamber. Journal of the American Rocket Society. 1952; 22(5): 263–268.
2. Swithenbank J, Sotter G. Vortices in solid propellant rocket motors. Jr. of AIAA. 1963; 1(7): 1682–1684.
3. Flandro GA, Jacobs HR. Vortexgeneration sound in cavities. AIAA Paper. 1973; 73–1014.
4. Culic FEC. Stability of high frequency pressure oscillation in rocket combustion chamber. Jr. of AIAA. 1963; 1(5): 1097–1104.
5. Baum JD. Numerical techniques for solving nonlinear instability problems in solid rocket motors. Jr. of AIAA. 1982; 21(7): 959–961.
6. Bernardini, M., Cimini, M., Stella, F., Carallini, E., Mascio, A. D., Neri, A., Salvadore, F., and Martell, E., “Implicit Large eddy simulation of Solid Rocket Motors using the immersed boundary method”, AIAA Propulsion and Energy, 2021, Aug. 911, 2021, USA.
7. Anthoine, J., Mettenleiter, M., Repellin, O., Buchlin, J.M., and Candel, S., “Influence of adaptive control on vortex driven instabilities in a scaled model of solid propellantmotors”, Jr. of Sound and Vibration, Vol. 262, Is. 5, may 2003, pp.10091046.
8. Kailasanath, K., Gardner, J. H., Boris, J. P. and Oran, E. S., “Numerical simulations of acousticvortex interactions in a centraldump ramjet combustor”, Jr. of Propulsion and Power, Vol. 3, No. 6, 1987, pp. 525533.
9. Menon, S., “Numerical simulations of oscillatory cold flows in an axisymmetric ramjet combustor”, Jr. of Propulsion and Power, Vol. 6, No. 5, 1990, pp. 525534 10. Flandro, G. A., “Effectives of vorticity on rocket combustion stability”, Jr. of Propulsion and Power, Vol. 11, No. 4, 1995, pp. 607625.
11. Wu WJ, Kung LC. Determination of triggering condition of vortexdriven acoustic combustion instability in rocket motors. Jr. of Propulsion and Power. 2000; 16(6): 1022–1029.
12. Vuillot, F., “Vortexshedding phenomena in solid rocket motor”, Jr. of Propulsion and Power, Vol. 11, No. 4, 1995, pp. 626639.
13. Kourta, A., “Computation of vortex shedding in solid rocket motors using time dependent turbulence model”, Jr. of Propulsion and Power, Vol. 15, No. 3, 1999, pp. 390405.
14. Wu, W. J. and Kung, L. C., “Determination of triggering condition of vortexdriven acoustic combustion instability in rocket motors”, Jr. of Propulsion and Power, Vol. 16, No. 6, 2000, pp. 10221029.
15. Radavich, P. M. and Selamet, A., “A computational approach for flowacoustic coupling in closed side branches”, Jr. of Acoustical Soc. of America, Vol. 109, No. 4, 2001, pp. 13431353.
16. Matveev, K. I. and Culic, F. E. C., “A model for combustion instability involving vortex shedding”, Jr. of Combustion Science and Tech., Vol. 175, No. 6, 2003, pp. 10591083.
17. Shanbhogue, S. J., Sujith, R. I. and Chakravarthy, S. R., “Aero acoustics of rocket motors with FINOCYL grain”, AIAA Paper 20034632, 39 th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. and Exhibit, 2003.
18. Kourta, A., “Instability of channel flow with fluid injection and parietal vortex shedding”, Jr. of Computers & Fluid, Vol.33, Is. 2, Feb. 2004, pp.155178.
19. Hirschbeg, L.., Schuller, T., Collinet, J., Schram, C., and Hirschberg, A., “Analytical Model for the prediction of perturbationsin a cold gas scale model of solid rocket motor”, Jr. of Sound and vibration, Vol.419, 2018, pp. 452468.
20. Tahorinezhad, R. and Zarepour, G., “Evaluation of vortex shedding phenomena in a subscaled rocket motor”, Jr. of Aerospace Sci. and Tech., Vol. 107, 2021, pp. 1324.
21. Vuillot, F., “Vortex shedding phenomena in solid rocket motors”, Jr. of Propulsion and Power, Vol. 11, No. 4, JulyAugust, 1995, pp. 626636.
22. Durojaye, R.O., “Cold flow simulation of vortex shedding in a segmented solid rocket motor”, A Ph.D. Thesis Submitted at The University of Alabama, USA.
23. Dupays, J., Prevost, M., Tarrin, P., and Vuillot, F, Effect of particulate phase on vortex shedding driven oscillation in solid rocket motor”, AIAA Meeting Paper, July 1996, AIAA Paper 963248, pages 14.
24. Vetel, J., Plourde, F., and DoanKim, S., “Characterization of a coupled phenomenon in a confined shearlayer”, International Journal of Heat and Fluid Flow, Vol. 23, Is 4, Aug. 2002, pp. 533543.
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Journal Menu
Editors Overview
joeam maintains an Editorial Board of practicing researchers from around the world, to ensure manuscripts are handled by editors who are experts in the field of study.
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P.K. Dash, Siddalingappa P.K, Lavanya S.
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Abstract
nCombustion instability is a major problem in most solid rocket motor (SRM) during its operation. More form of instability is generated due to several factors like coupling of combustion acoustic waves with flow dynamics, grain configuration, combustion chamber design, combustible mixture, etc. This type of flow turbulence is sustained in such system for long durations and leads to failure of the mission. In this paper, an effort has been made to understand the vortex shading inside the rocket motor through cold flow analysis. A computational model is designed and run in a platform of fluid flow analysis software FLUENT. The vortex generated at the dead end of combustion chamber has been determined under laminar and turbulent flow conditions. A scaletoscale model of Shanbhogue’ experimental setup has been developed and grid to two different number of cells, i.e., 40000 and 60000 respectively. Comparison of computational and experimental results and influence of number of cells on computational results have been determined in present investigation. The effect of perturbation in an unsymmetric fluid flow is estimated and sizable changes are noted on the pressure waves at vortex point with respect to flow behavior i.e., laminar and turbulent. All results are presented in form of table and graphs.n
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Keywords: Combustion instability, laminar, SRM, turbulent, vortex shedding
n[if 424 equals=”Regular Issue”][This article belongs to Journal of Experimental & Applied Mechanics(joeam)]
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Full Text
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Browse Figures
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References
n[if 1104 equals=””]
1. Elias I, Gordon R. Vibration of gas at ambient pressure in a rocket thrust chamber. Journal of the American Rocket Society. 1952; 22(5): 263–268.
2. Swithenbank J, Sotter G. Vortices in solid propellant rocket motors. Jr. of AIAA. 1963; 1(7): 1682–1684.
3. Flandro GA, Jacobs HR. Vortexgeneration sound in cavities. AIAA Paper. 1973; 73–1014.
4. Culic FEC. Stability of high frequency pressure oscillation in rocket combustion chamber. Jr. of AIAA. 1963; 1(5): 1097–1104.
5. Baum JD. Numerical techniques for solving nonlinear instability problems in solid rocket motors. Jr. of AIAA. 1982; 21(7): 959–961.
6. Bernardini, M., Cimini, M., Stella, F., Carallini, E., Mascio, A. D., Neri, A., Salvadore, F., and Martell, E., “Implicit Large eddy simulation of Solid Rocket Motors using the immersed boundary method”, AIAA Propulsion and Energy, 2021, Aug. 911, 2021, USA.
7. Anthoine, J., Mettenleiter, M., Repellin, O., Buchlin, J.M., and Candel, S., “Influence of adaptive control on vortex driven instabilities in a scaled model of solid propellantmotors”, Jr. of Sound and Vibration, Vol. 262, Is. 5, may 2003, pp.10091046.
8. Kailasanath, K., Gardner, J. H., Boris, J. P. and Oran, E. S., “Numerical simulations of acousticvortex interactions in a centraldump ramjet combustor”, Jr. of Propulsion and Power, Vol. 3, No. 6, 1987, pp. 525533.
9. Menon, S., “Numerical simulations of oscillatory cold flows in an axisymmetric ramjet combustor”, Jr. of Propulsion and Power, Vol. 6, No. 5, 1990, pp. 525534 10. Flandro, G. A., “Effectives of vorticity on rocket combustion stability”, Jr. of Propulsion and Power, Vol. 11, No. 4, 1995, pp. 607625.
11. Wu WJ, Kung LC. Determination of triggering condition of vortexdriven acoustic combustion instability in rocket motors. Jr. of Propulsion and Power. 2000; 16(6): 1022–1029.
12. Vuillot, F., “Vortexshedding phenomena in solid rocket motor”, Jr. of Propulsion and Power, Vol. 11, No. 4, 1995, pp. 626639.
13. Kourta, A., “Computation of vortex shedding in solid rocket motors using time dependent turbulence model”, Jr. of Propulsion and Power, Vol. 15, No. 3, 1999, pp. 390405.
14. Wu, W. J. and Kung, L. C., “Determination of triggering condition of vortexdriven acoustic combustion instability in rocket motors”, Jr. of Propulsion and Power, Vol. 16, No. 6, 2000, pp. 10221029.
15. Radavich, P. M. and Selamet, A., “A computational approach for flowacoustic coupling in closed side branches”, Jr. of Acoustical Soc. of America, Vol. 109, No. 4, 2001, pp. 13431353.
16. Matveev, K. I. and Culic, F. E. C., “A model for combustion instability involving vortex shedding”, Jr. of Combustion Science and Tech., Vol. 175, No. 6, 2003, pp. 10591083.
17. Shanbhogue, S. J., Sujith, R. I. and Chakravarthy, S. R., “Aero acoustics of rocket motors with FINOCYL grain”, AIAA Paper 20034632, 39 th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. and Exhibit, 2003.
18. Kourta, A., “Instability of channel flow with fluid injection and parietal vortex shedding”, Jr. of Computers & Fluid, Vol.33, Is. 2, Feb. 2004, pp.155178.
19. Hirschbeg, L.., Schuller, T., Collinet, J., Schram, C., and Hirschberg, A., “Analytical Model for the prediction of perturbationsin a cold gas scale model of solid rocket motor”, Jr. of Sound and vibration, Vol.419, 2018, pp. 452468.
20. Tahorinezhad, R. and Zarepour, G., “Evaluation of vortex shedding phenomena in a subscaled rocket motor”, Jr. of Aerospace Sci. and Tech., Vol. 107, 2021, pp. 1324.
21. Vuillot, F., “Vortex shedding phenomena in solid rocket motors”, Jr. of Propulsion and Power, Vol. 11, No. 4, JulyAugust, 1995, pp. 626636.
22. Durojaye, R.O., “Cold flow simulation of vortex shedding in a segmented solid rocket motor”, A Ph.D. Thesis Submitted at The University of Alabama, USA.
23. Dupays, J., Prevost, M., Tarrin, P., and Vuillot, F, Effect of particulate phase on vortex shedding driven oscillation in solid rocket motor”, AIAA Meeting Paper, July 1996, AIAA Paper 963248, pages 14.
24. Vetel, J., Plourde, F., and DoanKim, S., “Characterization of a coupled phenomenon in a confined shearlayer”, International Journal of Heat and Fluid Flow, Vol. 23, Is 4, Aug. 2002, pp. 533543.
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Journal of Experimental & Applied Mechanics
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Volume  13 
Issue  1 
Received  May 14, 2022 
Accepted  July 18, 2022 
Published  July 26, 2022 
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