Numerical Simulation of Flow in a Solid Rocket Motor: Combustion Coupled Pressure Dependent Regressive Boundary

Journal Title: International Journal of Engineering and Science Invention - Year 2018, Vol 6, Issue 3

Abstract

Acomputational study is performed for the simulation of reactive fluid flow in a solid rocket motor chamber with pressure dependent propellant burning surface regression. The model geometry consists of a 2D end burning lab-scale motor. Complete conservation equations of mass, momentum, energy and species are solved with finite rate chemistry. The pressure dependent regressive boundary in the combustion chamber is treated by use of remeshing techniques. Hydrogen and propane combustion processes are examined. Time dependent pressure and burning rate variations are illustrated comprehensively. Temperature and species mass fraction variations are given within the flame zone. Temperature, velocity and density distributions are compared for both constant burning rate and pressure dependent burning rate simulations.

Authors and Affiliations

Mehmet Ozer Havlucu, Kadir Kirkkopru

Keywords

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  • EP ID EP402938
  • DOI -
  • Views 85
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How To Cite

Mehmet Ozer Havlucu, Kadir Kirkkopru (2018). Numerical Simulation of Flow in a Solid Rocket Motor: Combustion Coupled Pressure Dependent Regressive Boundary. International Journal of Engineering and Science Invention, 6(3), 54-65. https://europub.co.uk/articles/-A-402938