Numerical Prediction of Two-Phase Reacting Flow Field and Performance in an Aeroengine Combustor
Publication: Journal of Aerospace Engineering
Volume 25, Issue 2
Abstract
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.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 25 • Issue 2 • April 2012
Pages: 151 - 160
Copyright
© 2012. American Society of Civil Engineers.
History
Received: May 30, 2009
Accepted: Jan 13, 2011
Published online: Jan 15, 2011
Published in print: Apr 1, 2012
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