Numerical simulation of highly-swirling supersonic flow inside a Laval nozzle

摘要

A high speed compressible gas was introduced tangentially into an adiabatic convergent-divergent nozzle, thus a highly swirling supersonic compressible flow was formed. Numerical simulations were carried out of the flow situations with various inlet swirling intensity. Both temperature and velocity distributions inside the nozzle are obtained. The average centrifugal acceleration at the nozzle outlet is computed and its relation with the inlet centrifugal acceleration was analysed. It was found that although shock wave may well exist at the nozzle throat, the swirling intensity or vorticity can still be enlarged by a factor of 2 to 10 at the nozzle outlet.