Velocity and low frequency combustor pressure oscillations have been measured in a ramjet dump combustor model. The mean and RMS values of the turbulent velocity field were obtained using a two-component LDV system operating in the backscatter mode. Reacting flow data were obtained for a premixed propane/air, while isothermal results were collected replacing the propane with nitrogen. The velocity data indicated substantial differences between the two cases. Combustor pressure oscillation data were obtained utilizing high frequency dynamic pressure transducers. The intensity and frequency of the oscillations were measured as a function of inlet velocity, combustor length, and equivalence ratio. Results showed that pressure oscillations were controlled by both vortex kinetics in the cumbustor and acoustic response of the inlet section.
Premixed, turbulent combustion of axisymmetric sudden expansion flows
Turbulente Verbrennung in vorgemischten axialsymmetrischen Strömungen bei plötzlicher Expansion
Joint Army-Navy-NASA-Air Force (JANNAF) Propulsion Meeting, 1990 ; 1 , Sep ; 305-312
1991
8 Seiten, 11 Bilder, 2 Tabellen, 8 Quellen
Conference paper
English
Rotation effects on axisymmetric sudden-expansion flows
AIAA | 1988
|Calculation of Axisymmetric Sudden Expansion Laminar Flows
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