Cavity-Based Injector Mixing Experiments for Supersonic Combustors With Implications on Igniter Placement (Postprint)
Abstract
Mixing experiments using simultaneous acetone and NO PLIF were performed in the AFRL/PRA Test-cell 19 supersonic wind tunnel. These experiments investigated the influence of simulated plasma-torch placement in an injector-cavity configuration exposed to a supersonic crossflow. Both the simulated plasma torch and fuel injector holes injected room temperature air, respectively seeded with acetone and nitric oxide (NO). Experiments at the streamwise centerline of the rectangular wind tunnel investigated the differences between an aero-ramp and a single 15-degree downstream-angled injector in coupling to the recirculating flow in a downstream cavity. The influence of wall effects were investigated with a similar single-hole injector placed 3.5 injector diameters from the sidewall of the rectangular duct. Simulated plasma torch holes were tested up and downstream of the injectors, all upstream of the cavity. Tests took take place in a uniform Mach-2 crossflow; the respective tunnel total pressure and temperature were 1.7 atmospheres and 530 K.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 2006
- Accession Number
- ADA464135
Entities
People
- Andrew C. Dwenger
- Campbell D. Carter
- Lance S. Jacobsen