In a three-dimensional arbitrary curvilinear coordinate system, a FORTRAN program was used to research a condition’s influence on an aeroengine’s two-phase reacting flow field and combustion performance. In this program, an algebraic stress model was adopted to simulate turbulence viscosity. A second-order moment eddy–break up turbulence combustion model was used to determine the chemical reaction rate. In a nonstaggered grid system, the governing equations for the gas phase were solved by the PISO algorithm, and simulation of gas-liquid coupling was achieved by using the particle-source-in-cell method. The aeroengine combustor’s performance was estimated by using an empirical-analytical design methodology. It can be observed that performance at maximum conditions is better than that at idling conditions. The obtained agreement between simulation results and rig-test data is reasonable, which indicates the reliability of the numerical program adopted in this paper. This special-purposed program can be used to predict combustor’s flow field and its performance for the optimization design of a modern aeroengine combustor.
Numerical Prediction of Two-Phase Reacting Flow Field and Performance in an Aeroengine Combustor
Journal of Aerospace Engineering ; 25 , 2 ; 151-160
2011-01-15
102012-01-01 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Numerical Prediction of Two-Phase Reacting Flow Field and Performance in an Aeroengine Combustor
Online Contents | 2012
|Prediction of Noise Source for an Aeroengine Combustor
AIAA | 2011
|Prediction of Combustion Noise for an Aeroengine Combustor
Online Contents | 2014
|