WSEAS Transactions on Heat and Mass Transfer
Print ISSN: 1790-5044, E-ISSN: 2224-3461
Volume 15, 2020
Modeling of Detonation Processes in Propulsion Engine
Author:
Abstract: Numerical modeling of chemically reacting gas flow in the propulsion chamber using the Navier-Stokes equations has been performed. The simplest form of the chamber has been used, when the last one represents axially symmetrical plane disk. Fuel and oxidant were fed into the chamber separately with outflow to the periphery. The directions of fuel and oxidizer jets are not at right angles to the inflow surface and not parallel one to another to supply better mixing of species. The detonation triggering depends on the values of angles between fuel and oxidizer jets. At parallel directions of the jets significant part of not reacted gas components leaves the chamber. This type of the propulsion chamber is more effective than one studied before, because of absence of stagnation zones and good mixing of species before burning. The diameter of the chamber may be done less, since the largest part of fuel reacted at the inlet surface.
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Pages: 130-137
DOI: 10.37394/232012.2020.15.17