Abstract
The present paper describes the numerical as well as the experimental study on the axisymmetric supersonic jet associated with a sootblower nozzle for boiler cleaning. The navier-Stokes equations are solved numerically, and the experimental work is also performed with the low-density wind tunnel. Calculations and experiments both cover the region from the nozzle exit to the downstream distance of 20 times the nozzle exit diameter. The effect of the nozzle divergence angle is discussed by comparing the experiments with calculations, and it is pointed out that, even when the expansion ratio across the nozzle is correct, the regular shock-cell structure appears in the jet for the nozzles with finite divergence angles. Also, the present numerical results on the impact pressures along the jet center-line agree favorably well with those reported by the other researchers.
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