Accession Number : ADA292414
Title : Flow Visualization of Vorticity Cancellation of Jets in Crossflow.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
Personal Author(s) : Simpson, Anthony G.
PDF Url : ADA292414
Report Date : MAR 1995
Pagination or Media Count : 110
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.
Descriptors : *FLOW VISUALIZATION, *JET FLOW, VELOCITY, INJECTION, RATIOS, FLUORESCENCE, TEST EQUIPMENT, VORTICES, LASERS, COOLING, LOW VELOCITY, FLOW FIELDS, LENGTH, COLORS, SHEETS, WIND TUNNEL TESTS, RIGGING, TURBINES, FLOW, DYES, LIFT, CANCELLATION, FILM COOLING, CROSS FLOW.
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE