Characterization of supersonic mixing in a nonreacting Mach 2 combustor

Conference · Tue Dec 31 23:00:00 EST 1991

OSTI ID:5454330

Hollo, S D; Mcdaniel, J C; Hartfield, JR, R J ^[1]

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1. Virginia, University, Charlottesville (United States)

Planar measurements of the injection mole fraction distribution and the velocity field within a nonreacting model SCRAMJET combustor have been made using laser-induced iodine fluorescence. The combustor geometry investigated in this work is staged transverse injection of air into a Mach 2 freestream. A complete three-dimensional survey of the injectant mole fraction distribution has been generated and a single planar velocity measurement has been completed. The measurements reveal the dramatic effect of streamwise vortices on the mixing of the injectant in the near field of the injectors, as well as the rapid mixing generated by staging two field injectors. Analysis of the downstream decay of the maximum injectant mole fraction in this and other nonreacting combustor geometries indicates that the relative rate of injectant mixing well downstream of the injectors is independent of combustor geometry, combustor Mach number, and injectant molecular weight. Mixing within this region of the combustor is dominated by turbulent diffusion within the injectant plume. The transition of the dominant mixing mechanism, from vortex-driven mixing in the near field to turbulent diffusion in the far field, was found to occur in the region between 10 and 20 jet diameters downstream of the injectors. 22 refs.

• Research Organization: Virginia Univ., Charlottesville, VA (United States)
• OSTI ID: 5454330
• Report Number(s): CONF-920157--; AIAA-Paper--92-0093
• Country of Publication: United States
• Language: English

Related Subjects

37 INORGANIC, ORGANIC, PHYSICAL, AND ANALYTICAL CHEMISTRY
400800* -- Combustion
Pyrolysis
& High-Temperature Chemistry
COMBUSTION CHAMBERS
COMPUTER CODES
DIFFUSION
ENGINES
FLOW MODELS
FLUID FLOW
FLUORESCENCE
FUEL INJECTION SYSTEMS
FUEL SYSTEMS
FUELS
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
JETS
LUMINESCENCE
MACH NUMBER
MATHEMATICAL MODELS
MIXING
MOLECULAR WEIGHT
RAMJET ENGINES
S CODES
SUPERSONIC FLOW
TURBULENT FLOW
VELOCITY
VORTEX FLOW