Micro-flow properties of NEPE propellant in a rotating depressurization combustion environment of solid rocket motor

Abstract

A profound understanding of microflow processes within the combustion chamber is paramount for optimizing engine performance and ensuring safe operation in the realm of solid rocket propulsion. Specifically, the scrutiny of Nitrate Ester Plasticized Polyether (NEPE) propellant under rotating depressurization combustion conditions has garnered substantial scholarly interest. The non-uniform distribution of propellant constituents and the ensuing heterogeneity in combustion rates convolve fluid flow dynamics within the chamber, ultimately engendering intricate flow patterns, turbulent phenomena, and rotational effects. Hence, conducting numerical simulation studies assumes an imperative role in comprehensively analyzing and apprehending the intricate microflow characteristics under such demanding circumstances. This paper endeavors to accomplish this overarching objective by introducing a novel kinetic mechanism in the gas phase that meticulously accounts for complicated reactions between distinct oxidizing powders and fuel binders, representing an uncharted territory in the existing literature. Additionally, this study takes into meticulous consideration the influence of radiation effects and non-planar moving surfaces, as well as other pivotal components. Upon establishing the combustion model, exponential depressurization is induced within the gas phase, while the computational domain is deflected to accurately simulate the rotational effects. A series of methodical investigations is subsequently undertaken to validate the proposed numerical framework, yielding commendable predictive accuracy. Ultimately, this research meticulously examines the minute intricacies of microflow characteristics under such complex transient combustion conditions.