Development of a Combustor Flow Analysis. Part I. Theoretical Studies.
Final rept. 1 Jun-30 Sep 73,
UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CONN
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A computational procedure for calculating the coupled flow and chemistry within both can-annular and annular gas turbine combustors is presented. The procedure solves the time-averaged Navier-Stokes equations with coupled chemistry including the effects of turbulence and droplet vaporization and burning, using a novel field relaxation method developed at the United Aircraft Research Laboratories. Although a relatively simple turbulence model is employed in the procedure, modification to this model is easily implemented within the framework of the computational method. Computations of the flow and chemistry within both can-annular and annular gas turbine combustors, conducted using the procedure, are presented and compared with experimental data. The results of the comparisons with data are obscured by three-dimensional effects present in real gas turbine combustors. However, the indications are that, for combustors where has considerable potential. Author
- Combustion and Ignition
- Jet and Gas Turbine Engines