Numerical simulation of combustion in a hybrid rocket with liquefying fuels

Document Type

Conference Proceeding

Publication Date

1-1-2019

Abstract

The methodology and implementation for numerical transient analysis of combustion in a hybrid rocket with liquefying fuel is presented. In this work, both the solid-liquid and liquid-gas phase change problems are considered, by employing a decoupled model for combustion and melting phase change. All the governing equations and model implementations are carried out in the frame work of commercial software ANSYS-FLUENT. A 2-dimensional problem is solved, which involves oxidizer flow over a paraffin wax fuel slab and is compared with the experimental regression rate data. The objective of the analysis is to understand the effect of melt layer surface instability and liquid droplet entertainment on the effective vaporization rate of the fuel. The regression rate predicted by the finite rate combustion model was in close agreement with the experimental results while the Eddy dissipation model based on single step stochiometric overpredicted the regression rate. The melting model, based on temperature and vaporization input from combustion model, predicted couple of orders higher melting rate than the experimental observations. The possible reasons for this deviation and required amendments to the existing melting model are discussed in detail.

Publication Source (Journal or Book title)

AIAA Propulsion and Energy Forum and Exposition, 2019

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