Experimental investigation of a supersonic combustion flowfield employing staged transverse injection behind a rearward-facing step
- Florida, University, Gainesville (United States) Virginia, University, Charlottesville (United States)
An experimental investigation of a Mach 2 combustor has been conducted in order to characterize flow properties in a supersonic reacting flowfield. Hydrogen was injected transversely as staged, underexpanded jets behind a rearward facing step into a ducted Mach 2 air free stream. The effects of the chemical reaction on the supersonic flowfield was investigated using shadowgraphs, broadband flame emission photography, and planar laser-induced fluorescence of OH. The shadowgraphs indicated a strong affect of the heat release on the wave pattern in the combustor, with a significant increase in flowfield unsteadiness. The broadband flame emission photographs revealed large regions of no combustion in the vicinity of the fuel injectors where fuel/air mixing was insufficient to support combustion. These regions decreased in size as the free stream stagnation temperature was decreased for fixed hydrogen mass flow rate, consistent with an increase in the effective Q-ratio with combustion. The size of the zones containing OH in the planar fluorescence images also both increased as the main flow stagnation temperature was decreased. Reaction zones were found in the planar fluorescence images away from regions containing injectant in a non-reacting study of the same geometry, indicating that the pressure rise associated with the reaction forced a large redistribution of the fuel. 11 refs.
- Research Organization:
- Florida Univ., Gainesville, FL (United States)
- OSTI ID:
- 5396396
- Report Number(s):
- CONF-920157--; AIAA-Paper--92-0090
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
400800* -- Combustion
Pyrolysis
& High-Temperature Chemistry
CHEMICAL REACTIONS
COMBUSTION
COMBUSTION CHAMBERS
ELEMENTS
FLAMES
FLOW VISUALIZATION
FLUID FLOW
FLUORESCENCE
FUEL-AIR RATIO
HYDROGEN
HYDROXYL RADICALS
IMAGES
LUMINESCENCE
MACH NUMBER
NONMETALS
OXIDATION
RADICALS
STAGNATION
SUPERSONIC FLOW
THERMOCHEMICAL PROCESSES
VELOCITY