Abstract
The detailed mixing, combustion and ignition processes occurring in a flow field under the influence of resonant acoustic perturbations are discussed. These acoustic perturbations were created by a pulse combustor of the “Heimholtz” type.
During the first two-thirds of the resonant cycle the inlet jet forms a well-defined toroidal vortex that is phase-locked with the combustor cycle. This toroidal vortex is responsible for the convection and mixing of the reactants with the residual hot products. Although chemiluminescence is always present in quiescent regions of the combustor, none exists in the region of the reactants during injection. Moreover, the combustion of the fresh reactants begins late in the cycle along the outer edges of the rolled up toroidal vortex, and not in the quiescent regions of the flow. The combustion of the reactants moves into the center of this toroidal vortex where rapid uniform ignition and subsequent combustion of the fresh reactants occurs. Vortex dynamic modeling of this flow using a flamelet formulation for combustion shows that a principle ignition delay mechanism is that of fluid dynamic stretch. This highly strained flow field suppresses ignition during the injection part of the cycle providing a mechanism to thoroughly mix the fresh with residual products preparing them for a rapid, almost volumetric, combustion process initiated by thermal and/or radical ignition.
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Keller, J.O., Barr, P.K. (1996). Premixed Combustion in a Periodic Flow Field. In: Culick, F., Heitor, M.V., Whitelaw, J.H. (eds) Unsteady Combustion. NATO ASI Series, vol 306. Springer, Dordrecht. https://doi.org/10.1007/978-94-009-1620-3_2
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DOI: https://doi.org/10.1007/978-94-009-1620-3_2
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