Vortex Generation and Mixing in Three-Dimensional Supersonic Combustors
Abstract
The generation and evolution of the flow vorticity established by instream injector ramps in a high Mach number/high enthalpy scramjet combustor flowfield are described in detail for a number of computational cases. Classical fluid dynamic circulation is presented for these cases in order to clarify the spatial distribution and convection of the vorticity. The ability of the simulations to accurately represent Stokes law of circulation is discussed and shown. In addition, the conservation of swirl is presented for these flows. The impact of both turbulent diffusion and the vortex/ramp nonuniformity on the downstream mixing rate is clearly illustrated. A correlation over the length of the combustor between fuel-air mixing and a parameter called the vortex stirring length is demonstrated. Finally, computational results for a representative ramp injector are compared with experimental data. © 1995 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
Recommended Citation
D. W. Riggins and P. H. Vitt, "Vortex Generation and Mixing in Three-Dimensional Supersonic Combustors," Journal of Propulsion and Power, vol. 11, no. 3, pp. 419 - 426, American Institute of Aeronautics and Astronautics, Jan 1995.
The definitive version is available at https://doi.org/10.2514/3.23860
Department(s)
Mechanical and Aerospace Engineering
International Standard Serial Number (ISSN)
0748-4658
Document Type
Article - Journal
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 1995
