Flow aerodynamics modeling of an MHD swirl combustor: calculations and experimental verification
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 pressure-velocity 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 two-equation k-e 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.
- Research Organization:
- Massachusetts Institute of Technology, Cambridge, MA
- OSTI ID:
- 5552136
- Journal Information:
- J. Fluids Eng.; (United States), Vol. 104:3
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
30 DIRECT ENERGY CONVERSION
AERODYNAMICS
COMPUTER CALCULATIONS
FLOW MODELS
MHD GENERATORS
COMBUSTORS
COMPUTER CODES
DIFFERENTIAL EQUATIONS
FINITE DIFFERENCE METHOD
FLOW RATE
FLUID FLOW
NOZZLES
PRESSURE DROP
TURBULENT FLOW
VELOCITY
VORTEX FLOW
DIRECT ENERGY CONVERTERS
EQUATIONS
FLUID MECHANICS
ITERATIVE METHODS
MATHEMATICAL MODELS
MECHANICS
NUMERICAL SOLUTION
420400* - Engineering- Heat Transfer & Fluid Flow
300100 - Direct Energy Conversion- MHD Generators