PARAMETRIC STUDY OF COMBUSTION INSTABILITY IN A MULTI-INJECTOR ROCKET COMBUSTOR USING 2D PLANAR DETACHED EDDY SIMULATIONS

摘要

Accurate modeling of combustion dynamics in liquid rocket engines remains a formidable challenge. The prediction of combustion instability is extremely complex due to the interaction of physical phenomena at different time and spatial scales such as acoustics, turbulence, hydrodynamics, species diffusion, chemical reactions and heat transfer. Within the U.S. Air Force Center of Excellence on Multi-Fidelity Modeling of Combustion Dynamics framework, Purdue University, MIT, University of Michigan, and University of Wisconsin-Madison are collaborating to develop reduced order models (ROMs) and data-driven techniques to efficiently simulate and predict combustion instabilities in liquid engines. The project aims to integrate ROMs into a multi-fidelity model that can predict the stability characteristics of a full-scale LRE containing multiple injector elements and provide a tool for designers to efficiently characterize the combustion dynamics of liquid rocket engines in shorter times and lower computational cost.