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 scale-to-scale 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.
Keywords: Combustion instability, laminar, SRM, turbulent, vortex shedding
[This article belongs to Journal of Experimental & Applied Mechanics(joeam)]
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|Received||May 14, 2022|
|Accepted||July 18, 2022|
|Published||July 26, 2022|