Abstract
A new supersonic flow-type annular detonation combustor is designed in which steady oblique detonation waves in the channel are generated using a compression body in the form of a solid single-wound spiral with a constant pitch angle. A two-dimensional unsteady mathematical model of the reacting flow in this device is formulated. The flow dynamics at the start of the chamber operation and steady supersonic flow structures for a stoichiometric hydrogen-air flow with an inlet Mach number M0=5 are numerically investigated. Two-dimensional numerical simulation is carried out for different spiral angles and geometrical dimensions of the chamber. A bifurcation of steady flow structures with respect to the initial condition of the problem is observed.
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