Flow aerodynamics modeling of an MHD swirl combustor - Calculations and experimental verificationThe paper describes a computer code for calculating the flow dynamics of a 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 for 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 the efficient solution of the equations. The code produces as output the flow field map of the nondimensional stream function, axial and swirl velocity. It was found that the best location for seed injection to obtain a uniform distribution at the combustor exit is in the central location for seed injected at the entrance to the second stage combustor.
Document ID
19820028578
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Gupta, A. K. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Beer, J. M. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Louis, J. F. (MIT Cambridge, MA, United States)
Busnaina, A. A. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Lilley, D. G. (Oklahoma State University Stillwater, OK, United States)