Swirl Combustor Flow Visualization Studies in a Water Tunnel
Abstract
The flowfield in a highly swirling combustor with a Confinement Ratio of 1.0, a bypass flow (secondary downstream air injection), aspiration holes in the burner can and a large central hub was simulated. Data was collected from visualization with neutral density plastic beads in water, and velocity and turbulence level profiles measured in cold air tests. The baseline case produced little noticeable recirculation. Increasing the confinement ratio to a maximum of 2.1 either by insert rings or a larger burner can generally strengthened the central zone to a state of incipient recirculation. Use of a convergent/divergent outer ring after the swirl section had further beneficial effects. The bypass flow reduced the radial extent and intensified the central zone of incipient recirculation while confining the flow aerodynamically by shifting velocity peaks toward the axis. Extended central hubs, although having little effect on the flow in the burner can, produced a rotating helix in the afterburner. Aspiration holes reduced velocity levels along the wall.
- Publication:
-
Journal of Spacecraft and Rockets
- Pub Date:
- December 1983
- DOI:
- 10.2514/3.8589
- Bibcode:
- 1983JSpRo..20..574S
- Keywords:
-
- Combustion Chambers;
- Flow Distribution;
- Flow Visualization;
- Swirling;
- Water Tunnel Tests;
- Convergent-Divergent Nozzles;
- Flow Velocity;
- Gas Injection;
- Hot-Wire Anemometers;
- Secondary Flow;
- Turbulent Flow;
- Wall Flow;
- Water Flow;
- Fluid Mechanics and Heat Transfer