Accession Number:

ADA409216

Title:

Parallel Modeling of Three-Dimensional Scramjet Combustor and Comparisons with Experiment's Results

Descriptive Note:

Corporate Author:

RUSSIAN ACADEMY OF SCIENCES NOVOSIBIRSK INST OF THEORETICAL AND APPLIED MECHANICS

Personal Author(s):

Report Date:

2002-08-23

Pagination or Media Count:

9.0

Abstract:

In this paper a parallel simulation of an experimental dual-mode scramjet combustor configuration is presented. Turbulence is modeled with the kappa-epsilon two-equation turbulence model and a 7-species 8-equation kinetics model is used to model hydrogenair combustion. The conservation from of the Navier-Stokes equations with finite-rate chemistry reactions is solved using a diagonal implicit finite-volume method. Using about 3,12O,000 grid points the three-dimension flow-fields with equivalence ratio phi0.0 and 0.35 have been respectively simulated on the parallel computer system obtaining more detailed flow properties than the experiments results. Wall pressure comparisons between CFD and experiment show fair agreement. For phi0.35 the fuel-penetrating height of the seven injectors are different because of the effects of the boundary layer and the shock wave in the combustor. According to numerical results, if adjusting the locations of the injectors the combustion efficiency could be improved.

Subject Categories:

  • Computer Programming and Software
  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE