Bow Shock/Jet Interaction in Compressible Transverse Injection Flowfields

摘要

Transverse injection of a gaseous fuel stream into a supersonic flow appears schematically in Fig. 1. This sketch illustrates the features of the flowficld in a plane through the spanwise jet centerline, where a three-dimensional bow shock forms ahead of the jet and interacts with the approaching turbulent boundary layer, resulting in separation. Previous investigations of this flowfield have provided clear visualizations of the large-scale vortices formed at the interface between the freestream and injectant fluids.1"3 These eddies influenced the position of the bow shock.2 Some images also showed the region enclosed by the separation shock where the bow shock and turbulent boundary layer interact.l>2 This region contains locally high wall static pressures as found in both experiments4 and numerical predictions.5 Numerical investigations of a reacting transverse hydrogen jet in a supersonic airstream by Takahashi and Hayashi6 showed relatively high static temperatures occurring within this separated zone. Erosion of the injector wall could occur as a result of this local high temperature zone.