A Study of Acoustic Forcing on Gas Centered Swirl Coaxial Reacting Flows (Conference Paper with Briefing Charts)
Abstract
The reacting flow from a single gas-centered, swirl-coaxial injector was studied in an optically accessible, high-pressure chamber, with and without high-frequency acoustic perturbations. The gas-centered, swirl-coaxial injector employed liquid rocket engine relevant propellants of gaseous oxygen and RP-2. The reacting flow field behavior at an operating chamber pressure of 3.2 MPa and varying momentum flux ratios were investigated. High-speed shadowgraph images along with OH* and CH* chemiluminescence images were taken to capture the liquid fuel film, droplets, and flame response under acoustic excitation. For the acoustic forcing studies, low amplitude transverse standing waves typically below 5 of the chamber pressure were generated to simulate transverse combustion instabilities. Proper orthogonal decomposition and dynamic mode decomposition were performed on the high-speed shadowgraph and chemiluminescence images to detect the flame response to acoustic forcing, to which in-plane flapping motion was observed for acoustic forcing and rotating soot clouds were a large structures associated with the reacting flow field.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 09, 2017
- Accession Number
- AD1027081
Entities
People
- Douglas G. Talley
- John W. Bennewitz
- Mario Roa
- Stephen A. Schumaker
Organizations
- Air Force Research Laboratory