Studies of Finite-Rate Effects Relevant to Modeling of Liquid-Propellant Rocket Combustion Instabilities
Abstract
The goal of this project is to advance fundamental knowledge pertaining to the interplay of the acoustic field with the reactive flow in liquid-propellant rocket engines, enabling the development of advanced modeling tools for predicting the instability behavior in realistic scenarios. Our work combines numerical and modeling efforts in linear and nonlinear studies of unsteady flames, with a focus on the development and application of quasi-steady-state reduced-chemistry mechanisms to the development of submodels for the numerical computation of liquid-propellant rocket instabilities. Specific objectives include the generation and validation of advanced flamelet models for future use in improved LES calculations of acoustic combustion instabilities and the investigation of flame dynamics in the near-injector region, with the latter investigation specifically addressing propagation of partially premixed fronts along mixing layers.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 04, 2023
- Accession Number
- AD1230323
Entities
People
- Antonio Sanchez
Organizations
- University of California, San Diego