Abstract

The flow structure for various detonation regimes is numerically studied in a new flow-type supersonic annular detonation combustor. In the combustor with a new design, detonation burning of the reacting mixture is organized by using a compression body, 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 Mach number M0 = 3 at the combustor entrance. A mathematical model of the reacting flow in the combustor is developed in a two-dimensional unsteady formulation. The flow dynamics at the beginning of combustor operation and the structure of the steady flow in the combustor are numerically studied. Simulations are performed for various helix angles and combustor sizes. A bifurcation of the steady flow structures with respect to the initial conditions of combustor operations is detected for some combinations of the geometric parameters of the combustor.

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