Large Eddy Simulation based Studies of Reacting and Non-reacting Transverse Jets in Supersonic Crossflow

Jet in supersonic crossflow (JISC) provide ecient mixing and flame stabilization in su-personic combustion. A LES-DQMOM based comprehensive methodology was developed and calculated sonic jet in Mach 2.0 crossflow with momentum ratio of 0.5, 1.03, and 1.52. JISC configuration were matched to experiment from Air Force Research Laboratory.1 After careful validation of the code, flow feature of non-reacting and reaction JISC were studied including shock structures and interaction of vortical structures. 13 species Ethylene-air reaction was modeled using a DQMOM based combustion model. High temperature region near the wall upstream of the jet and the recirculated flow behind the barrel shock from the jet provided suitable condition of auto-ignition and flame stability. To ensure ecient and robust combustion inside scramjet engines, fuel injection and mixing has to be rapid due to the short residence time associated with the flow. Transverse jet injection is one design that accelerates fuel jet breakdown, leading to faster small scale mixing of fuel and oxidizer.2–5 Here, the fuel jet issues from an injector typically mounted on the combustor walls either normally or at an injection angle. In addition to rapid mixing, transverse jets also provide enhanced flame stabilization. The injection of a fuel jet into a supersonic crossflow leads to a strong bow shock at the interface of the two streams, which creates boundar