Simulation of Transverse Gaseous Injection Through Diamond Ports into Supersonic Freestream
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Numerical simulations were performed to study the secondary flow structures induced by transverse underexpanded sonic injection through diamond-shaped orifices in a supersonic (M = 2.0 and 5.0) crossflow. Two new vortex features were observed in the vicinity of the injector port when compared to circular injector ports. The first pair, which has the potential to serve as a mixing enhancement mechanism, was located near the leading edge of the injector. The second pair was located just downstream of the barrel shock. This gasdynamically induced flow structure, termed the lateral counter-rotating vortex pair, has the potential to act as a flame-holding device. It was observed that the lateral counter-rotating vortex pair did not form in simulations of angled transverse injection. However, the leading-edge vortex pair was found to be stronger in angled injection simulations. To combine the advantages of the leading-edge mixing and the lateral counter-rotating vortex pair structure, additional numerical simulations were performed with 27.5-90 deg and 45-90 deg hybrid injectors. The lateral counter-rotating vortex pair structure was observed in both of these simulations along with enhanced leading-edge mixing as compared to the normal injection case. Copyright 2007 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
Journal of Propulsion and Power
author list (cited authors)
Srinivasan, R., & Bowersox, R.
complete list of authors
Srinivasan, Ravichandra||Bowersox, Rodney DW