Flow aerodynamics modeling of an MHD swirl combustor  Calculations and experimental verification
Abstract
This paper describes a computer code for calculating the flow dynamics of constant density flow in the second stage trumpet shaped nozzle section of a two stage MHD swirl combustor for application to a disk generator. The primitive pressurevelocity variable, finite difference computer code has been developed to allow the computation of inert nonreacting turbulent swirling flows in an axisymmetric MHD model swirl combustor. The method and program involve a staggered grid system for axial and radial velocities, and a line relaxation technique for efficient solution of the equations. Turbulence simulation is by way of a twoequation Kappaepsilon model. The code produces as output the flowfield map of the nondimensional stream function, axial, and swirl velocity. Good agreement was obtained between the theoretical predictions and the qualitative experimental results. The best seed injector location for uniform seed distribution at combustor exit is with injector located centrally on the combustor axis at entrance to the second stage combustor.
 Publication:

ASME Journal of Fluids Engineering
 Pub Date:
 September 1982
 Bibcode:
 1982ATJFE.104..385G
 Keywords:

 Aerodynamic Characteristics;
 Combustion Chambers;
 Computational Fluid Dynamics;
 Magnetohydrodynamic Generators;
 Nozzle Flow;
 Codes;
 Finite Difference Theory;
 Flow Geometry;
 Flow Visualization;
 KEpsilon Turbulence Model;
 Swirling;
 Fluid Mechanics and Heat Transfer