Flow Visualization of Vorticity Cancellation of Jets in Crossflow.
Abstract
An experimental apparatus was designed and constructed for water tunnel flow visualization of multiple, staggered and in-line row jet injection in cross flow. Specifically, a physical explanation was sought for existing film cooling performance results from turbine test rigs. Experiments were conducted in the University of Washington low-speed, free surface water tunnel facility having a 3.0 x 0.7 x 0.7 meter test section and a speed capability of up to 0.7 rn/s. Jet injection was controlled for each row independently at blowing ratios from 0.5 to 2.5, with the jet development length to diameter ratio set at 6.0. Flow visualization using both colored dye and fluorescent laser sheeting was accomplished to track vortex structure and interaction in the flow. The results indicate that vorticity cancellation is a factor in improved cooling performance over single row injection through a reduction in both jet lift off from the surface and entrainment of the main flow toward the surface.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1995
- Accession Number
- ADA292414
Entities
People
- Anthony G. Simpson
Organizations
- Air Force Institute of Technology