Highly-swirling supersonic flows of compressible gases are common in various gas treatment and combustion systems. Very high vorticity or centrifugal acceleration of gas flow with very high velocity may be desired for efficient separation of heavy components from main gas flow. In this paper, a high speed compressible gas was introduced tangentially into an adiabatic convergent-divergent nozzle (a passage similar to a Laval nozzle), thus a highly swirling supersonic compressible flow was formed. Numerical simulations were carried out of the flow situations with various inlet swirling intensities. Both temperature and velocity distributions inside the nozzle are obtained under various flow conditions. The average centrifugal acceleration at the nozzle outlet is obtained and its relation with the inlet centrifugal acceleration was analyzed. It was found from our limited computation that although shock wave may well exist at the throat of the nozzle, the swirling intensity or vorticity can still be enlarged by a factor of 2 to10 at the outlet of the nozzle.
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