scholarly journals Modeling gaseous non-reactive flow in a lean direct injection gas turbine combustor through an advanced mesh control strategy

Author(s):  
R Payri ◽  
R Novella ◽  
M Carreres ◽  
M Belmar-Gil

Fuel efficiency improvement and harmful emissions reduction are the main motivations for the development of gas turbine combustors. Numerical computational fluid dynamics (CFD) simulations of these devices are usually computationally expensive since they imply a multi-scale problem. In this work, gaseous non-reactive unsteady Reynolds-Averaged Navier–Stokes and large eddy simulations of a gaseous-fueled radial-swirled lean direct injection combustor have been carried out through CONVERGE™ CFD code by solving the complete inlet flow path through the swirl vanes and the combustor. The geometry considered is the gaseous configuration of the CORIA lean direct injection combustor, for which detailed measurements are available. The emphasis of the work is placed on the demonstration of the CONVERGE™ applicability to the multi-scale gas turbine engines field and the determination of an optimal mesh strategy through several grid control tools (i.e., local refinement, adaptive mesh refinement) allowing the exploitation of its automatic mesh generation against traditional fixed mesh approaches. For this purpose, the normalized mean square error has been adopted to quantify the accuracy of turbulent numerical statistics regarding the agreement with the experimental database. Furthermore, the focus of the work is to study the behavior when coupling several large eddy simulation sub-grid scale models (i.e., Smagorinsky, Dynamic Smagorinsky, and Dynamic Structure) with the adaptive mesh refinement algorithm through the evaluation of its specific performances and predictive capabilities in resolving the spatial-temporal scales and the intrinsically unsteady flow structures generated within the combustor. This investigation on the main non-reacting swirling flow characteristics inside the combustor provides a suitable background for further studies on combustion instability mechanisms.

2010 ◽  
Vol 181 (2) ◽  
pp. 247-258 ◽  
Author(s):  
Thomas Unfer ◽  
Jean-Pierre Boeuf ◽  
François Rogier ◽  
Frédéric Thivet

2021 ◽  
Vol 33 (4) ◽  
pp. 045126
Author(s):  
Laura Pereira de Castro ◽  
Abgail Paula Pinheiro ◽  
Vitor Vilela ◽  
Gabriel Marcos Magalhães ◽  
Ricardo Serfaty ◽  
...  

Author(s):  
Aleksandra Rezchikova ◽  
Cédric Mehl ◽  
Scott Drennan ◽  
Olivier Colin

Abstract The accurate simulation of two-phase flow combustion is crucial for the design of aeronautical combustion chambers. In order to gain insight into complex interactions between a flame, a flow, and a liquid phase, the present work addresses the combustion modeling for the Large Eddy Simulation (LES) of a turbulent spray jet flame. The Eulerian-Lagrangian framework is selected to represent the gaseous and liquid phases, respectively. Chemical processes are described by a reduced mechanism, and turbulent combustion is modeled by the Thickened Flame Model (TFM) coupled to the Adaptive Mesh Refinement (AMR). The TFM-AMR extension on the dispersed phase is successfully validated on a laminar spray flame configuration. Then, the modeling approach is evaluated on the academic turbulent spray burner, providing a good agreement with the experimental data.


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