Abstract
The presented paper is devoted to the study of detonation structures in a flow-type supersonic chamber of a new design, previously proposed by us. The detonation chamber is an annular cylindrical channel located between the inner and outer cylindrical walls. The oblique detonation wave is formed by a compression body inside the annular channel, shaped as a continuous monofilar helix with a constant pitch angle. Numerical simulations are performed for a supersonic flow of a stoichiometric hydrogen-air mixture with inflow Mach number M0=3 and the pitch angle a<aCJ. A mathematical model of the reacting flow in the combustor is developed in a two-dimensional unsteady formulation. A two-stage model of the detonation kinetics is used to describe the chemical process in reacting gas. The flow evolution for the different conditions for starting the detonation chamber operation is numerically studied. The final structures of the steady flow in the combustor are obtained. The bifurcation effect of a stationary solution according to the initial conditions of the problem is discovered for some combinations of the geometric parameters of the detonation combustor.
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