Large eddy simulation of a confined jet diffusion flame using a finite difference method

2008 ◽  
Vol 8 (6) ◽  
pp. 379
Author(s):  
A.L. De Bortoli
Keyword(s):  
Finite Difference ◽  
Finite Difference Method ◽  
Large Eddy Simulation ◽  
Diffusion Flame ◽  
Difference Method ◽  
Eddy Simulation ◽  
Large Eddy

Validation of a Three-Dimensional Large Eddy Simulation Finite Difference Method to Study Vortex Induced Vibration

2006 ◽  
Author(s):  
Paulo T. Esperanc¸a ◽  
Juan B. V. Wanderley ◽  
Carlos Levi
Keyword(s):  
Experimental Data ◽  
Finite Difference ◽  
Finite Difference Method ◽  
Large Eddy Simulation ◽  
Difference Method ◽  
Three Dimensional ◽  
Two Dimensional ◽  
Vortex Induced Vibration ◽  
Eddy Simulation ◽  
Large Eddy

Two-dimensional numerical simulations of Vortex Induced Vibration have been failing to duplicate accurately the corresponding experimental data. One possible explanation could be 3D effects present in the real problem that are not modeled in two-dimensional simulations. A three-dimensional finite difference method was implemented using Large Eddy Simulation (LES) technique and Message Passage Interface (MPI) and can be run in a cluster with an arbitrary number of computers. The good agreement with other numerical and experimental data obtained from the literature shows the good quality of the implemented code.

scholarly journals A REDUCED KINETIC MECHANISM FOR PROPANE FLAMES

2012 ◽  
Vol 11 (1-2) ◽  
pp. 37
Author(s):  
G. S. L. Andreis ◽  
R. S. Gomes ◽  
A. L. De Bortoli
Keyword(s):  
Finite Difference ◽  
Finite Difference Method ◽  
Diffusion Flame ◽  
Difference Method ◽  
Kinetic Mechanism ◽  
Governing Equations ◽  
Propane Combustion ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Reduced Kinetic Mechanism

Propane is one of the simplest hydrocarbons that can be a representative of higher hydrocarbons used in many applications. Therefore, this work develops a ten-step reduced kinetic mechanism among 14 reactive species for the propane combustion. The model is based on the solution of the flamelet equations. The equations are discretized using the second-order space finite difference method, using LES (Large-Eddy Simulation). Obtained results compare favorably with data in the literature for a propane jet diffusion flame. The main advantage of this strategy is the decrease of the work needed to solve the system of governing equations.

Mixed Acoustic-Entropy Combustion Instabilities in a Model Aeronautical Combustor: Large Eddy Simulation and Reduced Order Modeling

2017 ◽  
Vol 140 (3) ◽  
Author(s):  
Florent Lacombe ◽  
Yoann Méry
Keyword(s):  
Large Eddy Simulation ◽  
Diffusion Flame ◽  
Combustion Process ◽  
Premixed Flame ◽  
Dynamic Mode Decomposition ◽  
Dynamic Mode ◽  
Combustion Instabilities ◽  
Eddy Simulation ◽  
Mode Decomposition ◽  
Large Eddy

This article focuses on combustion instabilities (CI) driven by entropy fluctuations which is of great importance in practical devices. A simplified geometry is introduced. It keeps the essential features of an aeronautical combustion chamber (swirler, dilution holes, and outlet nozzle), while it is simplified sufficiently to ease the analysis (rectangular vane, one row of holes of the same diameter, no diffuser at the inlet of the chamber, and circular nozzle at the outlet). A large eddy simulation (LES) is carried out on this geometry and the limit cycle of a strong CI involving the convection of an entropy spot is obtained. The behavior of the instability is analyzed using phenomenological description and classical signal analysis. One shows that the system can be better described by considering two reacting zones: a rich mainly premixed flame is located downstream of the swirler and an overall lean diffusion flame is stabilized next to the dilution holes. In a second step, dynamic mode decomposition (DMD) is used to visualize, analyze, and model the complex phasing between different processes affecting the reacting zones. Using these data, a zero-dimensional (0D) modeling of the premixed flame and of the diffusion flame is proposed. These models provide an extended understanding of the combustion process in an aeronautical combustor and could be used or adapted to address mixed acoustic-entropy CI in an acoustic code.

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