In an axisymmetric model of a solid rocket motor, a cylindrical combustion chamber with porous walls is considered. For a posited range of operating parameters, the energy equation is perturbed and linearized using the dimensionless Péclet number. The possibility of circumventing chemical reactions while retaining the essential physics of the problem is explored. This is accomplished by artificially introducing a distributed heat source above the propellant surface. The resulting energy equation is then solved to zeroth order. The analytical solution and corresponding temperature maps are verified qualitatively using comparisons with numerical simulations of the combustion chamber.

Issue Section:
Technical Briefs
Keywords:
temperature distribution, chemically reactive flow, combustion, confined flow, rocket engines, flow through porous media, heat transfer, asymptotic technique, thin sheet approximation, solid rocket motor, eigenfunction expansion
Topics:
Boundary-value problems, Combustion, Combustion chambers, Eigenfunctions, Flow (Dynamics), Heat, Motors, Rockets, Temperature, Temperature distribution, Propellants, Approximation, Chemical reactions, Flames, Computer simulation
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Copyright © 2007
 by American Society of Mechanical Engineers
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