Abstract
Current aerospace propulsion system development programs are driving combustion diagnostics development efforts in new directions. Miniaturization of the high-temperature flow-field probes is necessary in order to embed the diagnostic systems in the internal confines of the propulsion system configurations. A critical process necessary for the survival of metallic flow-field probes in a high-temperature combustion stream is the stable cooling of the probe structures. Typically, forced convective cooling using high-pressure, high-velocity subcooled water is incorporated into the flow-field probe hardware designs. Recent probe miniaturization efforts have included water-cooled structures with diameters less than 3 mm (0.12 in.). Although forced convection water cooling has permitted larger probe configurations to survive harsh combustion environments, the cooling process in miniaturized probe structures is expected to be somewhat different because of surface tension effects and coolant flow path dimensions approaching vapor bubble diameters when the coolant transitions into flow boiling at higher heat flux. The purpose of this paper is to present recent applications of miniature combustion probes, as well as cooling effectiveness predictions for representative cooling channel configurations and heating conditions appropriate for the miniature probe configurations.
Published Version
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