Engine-Level Simulation of Liquid Rocket Combustion Instabilities
Abstract
A numerical investigation into combustion instability in liquid rocket engines is undertaken using large eddy simulations (LES). HPCMP resources have been applied to demonstrate the ability to simulate combustion instability in liquid rocket engines and to gain further understanding of these complex phenomena. Specifically, simulations have been used to uncover the unsteady instability mechanism in a single‐element injector. Results show that it is a combination of three events that lead to the instability and the timing of the events are critical. A second investigation has begun to apply LES to multi‐element injectors, which require significant resources. Finally, an investigation into the use of approximate boundary conditions, relevant to multi‐element injectors, showed that caution must be used when applying approximate boundary conditions. The results show that approximate boundary conditions led to different heat release locations and mixing downstream of the boundary.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 2013
- Accession Number
- ADA596950
Entities
People
- Douglas G. Talley
- Suresh Menon
Organizations
- Air Force Research Laboratory