scholarly journals Computational study on the non-reacting flow in Lean Direct Injection gas turbine combustors through Eulerian-Lagrangian Large-Eddy Simulations

2020 ◽  
Author(s):  
Mario Belmar Gil
Keyword(s):  
Gas Turbine ◽  
Computational Study ◽  
Direct Injection ◽  
Large Eddy Simulations ◽  
Reacting Flow ◽  
Lean Direct Injection ◽  
Gas Turbine Combustors ◽  
Large Eddy

Large-Eddy Simulation of a Swirl-Stabilized, Lean Direct Injection Spray Combustor

2006 ◽  
Author(s):  
Mehmet Kırtas¸ ◽  
Nayan Patel ◽  
Vaidyanathan Sankaran ◽  
Suresh Menon
Keyword(s):  
Large Eddy Simulation ◽  
Vortex Breakdown ◽  
Direct Injection ◽  
Reacting Flow ◽  
Mean Velocity ◽  
Recirculation Bubble ◽  
Lean Direct Injection ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Recirculation Zones

Large-eddy simulation (LES) of a lean-direct injection (LDI) combustor is reported in this paper. The full combustor and all the six swirl vanes are resolved and both cold and reacting flow simulations are performed. Cold flow predictions with LES indicate the presence of a broad central recirculation zone due to vortex breakdown phenomenon near the dump plane and two corner recirculation zones at the top and bottom corner of the combustor. These predicted features compare well with the experimental non-reacting data. Reacting case simulated a liquid Jet-A fuel spray using a Lagrangian approach. A three-step kinetics model that included CO and NO is used for the chemistry. Comparison of mean velocity field predicted in the reacting LES with experiments shows reasonable agreement. Comparison with the non-reacting case shows that the centerline recirculation bubble is shorter but more intense in the reacting case.

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

2020 ◽  
Vol 234 (11) ◽  
pp. 1788-1810
Author(s):  
R Payri ◽  
R Novella ◽  
M Carreres ◽  
M Belmar-Gil
Keyword(s):  
Gas Turbine ◽  
Adaptive Mesh Refinement ◽  
Swirling Flow ◽  
Direct Injection ◽  
Mesh Refinement ◽  
Adaptive Mesh ◽  
Experimental Database ◽  
Lean Direct Injection ◽  
Multi Scale ◽  
Large Eddy

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.

CFD-Led Designs of Pre-Filming Injectors for Gas-Turbine Combustors

2018 ◽  
Author(s):  
Kumud Ajmani ◽  
Hukam Mongia ◽  
Phil Lee ◽  
Kathleen Tacina
Keyword(s):  
Gas Turbine ◽  
Parametric Design ◽  
Direct Injection ◽  
Flow Simulation ◽  
Interaction Model ◽  
Aerodynamic Characteristics ◽  
Reacting Flow ◽  
Gas Turbine Combustors ◽  
Main Injection ◽  
Design Integration

The National Combustion Code (OpenNCC) was used to perform parametric design and analysis for three iterations of pre-filming injector design for gas-turbine combustors. The CFD analysis had significant impact on the design, integration and fabrication of a third-generation Lean-Direct Injection (LDI-3) flame-tube assembly consisting of nineteen injection elements. The air passages of the three pilot elements and sixteen main injection elements consisted of CFD-optimized compound-angle discrete jets and dual axial-bladed swirl-venturi passages, respectively. The aerodynamic characteristics of the nineteen-element injection array were evaluated by performing non-reacting flow simulation using a Time-Filtered Navier-Stokes (TFNS) method. The pilot and main injection elements were fueled with conventional pressure-atomizers and newly designed pre-filming nozzles, respectively. Fuel-air mixing and combustion performance was evaluated with reacting-flow TFNS computations using a 14-species, 18-step reduced kinetics mechanism for Jet-A fuel, Lagrangian spray modeling and a PDF turbulent-chemistry interaction model. The TFNS reacting-flow simulations provided considerable insight into the correlation between aerodynamics, combustion and emissions performance of the newly-designed pilot and main injection elements for the LDI-3 combustor at simulated cruise conditions.

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