Abstract
The oscillatory motions of all field variables (pressure, temperature, velocity, density, and fuel fractions) in the flame zone of solid propellant rocket motors are calculated using the finite element method. The Arrhenius law with a single step forward chemical reaction is used. Effects of radiative heat transfer, impressed arbitrary acoustic wave incidence, and idealized mean flow velocities are also investigated. Boundary conditions are derived at the solid-gas interfaces and at the flame edges which are implemented via Lagrange multipliers. Perturbation expansions of all governing conservation equations up to and including the second order are carried out so that nonlinear oscillations may be accommodated. All excited frequencies are calculated by means of eigenvalue analyses, and the combustion response functions corresponding to these frequencies are determined. It is shown that the use of isoparametric finite elements, Gaussian quadrature integration, and the Lagrange multiplier boundary matrix scheme offers a convenient approach to two-dimensional calculations.
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References
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Chung, T.J., Kim, P.K. (1985). Unsteady combustion of solid propellants. In: Glowinski, R., Larrouturou, B., Temam, R. (eds) Numerical Simulation of Combustion Phenomena. Lecture Notes in Physics, vol 241. Springer, Berlin, Heidelberg. https://doi.org/10.1007/BFb0008659
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DOI: https://doi.org/10.1007/BFb0008659
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