Numerical and Experimental Investigations of the Fundamental Processes That Drive Combustion Instabilities In Liquid Rocket Engines
Abstract
The objective is to determine the relative driving of combustion instabilities provided by different injectors designs under different operating conditions in different LRE. This may provide industry with an approach for determining the most stable injectors system design for a given LRE, and the effect of the interactions of the combustion processes produced by different injectors upon the LRE stability, the effect of mean pressure upon the LRE stability, and the effect of such operating/design parameters as fuel/oxidizer ratios, fuel flow rates, asymmetries in injectors system design (i.e., one that employs an array of injectors that have small geometrical differences in their designs, a practice used by the Russian that seems to have positive effects on engine stability) upon the LRE stability. Stability of a premixed flame segment in an acoustic field generated by a diffusion flame segment: Here various instability modes such as DL, RT, DT and their interaction with the diffusion-flame generated acoustics will be considered.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 23, 2016
- Source ID
- FA95501510498
Entities
People
- Ben Zinn
Organizations
- Air Force Office of Scientific Research
- Georgia Tech Research Corporation
- United States Air Force