Reduced Reaction Mechanism for Rocket Nozzle Ablation Simulations

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Reduced Reaction Mechanism for Rocket Nozzle Ablation Simulations

Cross, Peter G. / Boyd, Iain D.

A reduced reaction mechanism suitable for modeling finite-rate gas-phase chemistry associated with the ablation of carbon-phenolic materials in rocket nozzle applications is presented. Important species are identified by performing equilibrium chemistry calculations over a range of conditions determined from decoupled ablation analyses of the High Internal Pressure-Producing Orifice nozzle. An investigation of the literature is performed to identify candidate reaction mechanisms that involve these species. Sensitivity studies are conducted in order to reduce a large combustion mechanism to a minimal essential set of species and reactions that can accurately model the postcombustion nozzle core flow and ablation products over the conditions of interest. This reduced mechanism is small (only 20 species and 33 reactions) so that it can be used in a flow solver as part of the conjugate ablation analyses of rocket nozzles. This mechanism is found to be adequate for modeling the flow through the nozzles of solid rocket motors using typical aluminized composite propellants, and it should be suitable for use in conjugate flowfield/ablation analyses of carbon-phenolic nozzles for nondimensional pyrolysis gas mass flux values up to 0.4, temperatures up to 3000 K, and pressures up to 6.0 MPa.