Dynamics of swirling jet flows

Ivanic, Tanja; Foucault, E.; Pécheux, J.

doi:10.1007/s00348-003-0646-5

Cited by 21 publications

(9 citation statements)

References 15 publications

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“…In a high swirl number flow where the azimuthal velocity is comparable to the axial velocity, vortex breakdown may take place. Several important studies on swirling flow instabilities and coherent vortex motions, including experimental investigations [128][129][130][131][132][133], theoretical analyses [134][135][136][137][138], and numerical simulations [139][140][141][142][143][144], have been recently reported. Liang and Maxworthy [133] performed a notable experimental study of swirling jets, in which swirl is generated using a long rotating tube.…”

Section: • Lows Wirl Numbermentioning

confidence: 99%

Dynamics and stability of lean-premixed swirl-stabilized combustion

Huang

Yang

2009

Progress in Energy and Combustion Science

1,093

459

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Section: • Lows Wirl Numbermentioning

confidence: 99%

Dynamics and stability of lean-premixed swirl-stabilized combustion

Huang

Yang

2009

Progress in Energy and Combustion Science

1,093

459

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“…The degree of mixing depends mainly on the intensity of the swirl, defined by the swirl number S W , which can be expressed according to equation (7) 61 …”

Section: Numerical Results: Validation and Discussionmentioning

confidence: 99%

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

Payri

Novella

Carreres

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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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.

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“…Inlet conditions are calculated from the experimental data according to Ivanic [45] and Fitzgerald et al [37], at a distance x 0 = x/D i = 0.25.…”

Section: Resultsmentioning

confidence: 99%