Active Control Strategies to Optimize Supersonic Fuel-Air Mixing for Combustion Associated with Fully Modulated Transverse Jet in Cross Flow
Abstract
A 76 mm x 76 mm supersonic wind tunnel with variable Mach Numbers (M = 1.5 - 4) was designed and set up. The wind tunnel could support both non-reacting fuel-air mixing and combustion. A back pressure flap was added at the downstream end of the diffuser for dual mode (subsonic- supersonic) combustion studies. A high-speed imaging system was used for the visualization of pure liquid jet, aerated liquid jet and pulsed aerated jet injection into a supersonic cross flow at Mach number 1.5. The penetration height of the jet was determined from the average of 100 instantaneous recorded images. For the aerated jet the gas-liquid mass ratio varied from 0 to 8.2% for water and from 0 to 9.9% for methanol. For the pulsed aerated jet, the aerating gas was pulsed with a frequency range 1 - 1000 Hz at a constant duty cycle of 50% and at 1000 Hz with a variable duty cycle between 0 and 100%. Results were reported in correlations.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 27, 2005
- Accession Number
- ADA443378
Entities
People
- C. Ghenai
- C. X. Lin
- G. P. Philippidis
Organizations
- Florida International University