Shock-Wave/Boundary-Layer Interactions in Rotating Detonation Combustors

This computational study examines shock-wave/boundary-layer interactions in a transition duct that converts flow exiting a rotating detonation combustor (RDC) with oblique shock waves that propagate circumferentially in an annulus from supersonic to subsonic speeds via a terminal shock. The computations is based on the time dependent, three-dimensional ensemble-averaged continuity, Navier Stokes, and energy equations (unsteady RANS) for a thermally-perfect gas with temperature-dependent viscosity, thermal conductivity, and specific heats that are closed by the shear-stress transport model. An extension duct with a buffer and a sponge layer was appended to the exit of the transition duct to ensure no spurious waves form at the exit of the transition duct. Results obtained show how rise in pressure and temperature and how change in flow direction induced by the spiraling oblique shock wave (SSW) control flow separation induced by the terminal shock (TS) and prevent unstart. Results obtained also show the SSW to scrape and to deflect the flow in the separated region upstream of the SSW along the TS as it spirals.