A Large-Eddy-Simulation Study of Combustion Dynamics of Bluff-Body Stabilized Flames

Li, Huaguang; Khare, Prashant; Sung, Hong-Gye; Yang, Vigor

doi:10.1080/00102202.2015.1136296

Cited by 35 publications

(13 citation statements)

References 50 publications

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“…The Volvo configuration has also been ex-tensively studied numerically by other researchers through LES over the past two decades. Among the more recent efforts, the investigation on the effect of numerical methods include the series of simulations performed by Cocks et al [11,12], in which the results produced by four FV-based solvers using different numerics are compared against each other and experimental data, and the work of Li et al [13], which studies the effect of reflecting and non-reflecting inlets on combustion dynamics. The self-excited combustion instabilities in this configuration were studied by Ghani et al [14].…”

Section: Introductionmentioning

confidence: 99%

MVP-Workshop Contribution: Modeling of Volvo bluff body flame experiment

Peter

et al. 2017

55th AIAA Aerospace Sciences Meeting

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The Volvo burner features the canonical configuration of a bluff-body stabilized premixed flame. This configuration was studied experimentally under the Volvo Flygmotor AB program. Two cases are considered in this study: a non-reacting case with an inlet flow speed of 16.6 m/s and a reacting case with equilibrium ratio of 0.65 and inflow speed of 17.3 m/s. The characteristic vortex shedding in the wake behind the bluff body is present in the non-reacting case, while two oscillation modes are intermittently present in the reacting case. A series of large-eddy simulations are performed on this configuration using two solvers, one using a high-resolution finite-volume (FV) scheme and the other featuring a high-order discontinuous-Galerkin (DG) discretization. The FV calculations are conducted on hexahedral meshes with three different resolution (4mm, 2mm, and 1mm). The DG calculations are performed using two different polynomial orders on the same tetrahedral mesh. For the non-reacting cases, good agreement with respect to the experimental data is achieved by both solvers at high numerical resolution. The reacting cases are calculated using a two-step global mechanism in combination with the thickened-flame model. Reasonable agreement with experiments is obtained by both solvers at higher resolution. Models for combustion-turbulence interaction are necessary for the reacting case as it contains the length scale of the flame, which is smaller than the grid resolution in all calculations. The impact of such models on the flame stability and flow/flame dynamics is the subject of future research.

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Section: Introductionmentioning

confidence: 99%

MVP-Workshop Contribution: Modeling of Volvo bluff body flame experiment

Peter

et al. 2017

55th AIAA Aerospace Sciences Meeting

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“…However, as extensively shown in past studies, flows behind a step are dominated by large-scale spanwise vortices having quasi two-dimensional structures in the near field. 17,20,50) It was also shown that the turbulence energy spectra correspond to that of two-dimensional mixing layers, and thus two-dimensional treatment of the computational do-main usually well predicts experimental results. 50) Therefore, it is expected that two-dimensional simulations lose three-dimensional turbulent structures, but captures the large-scale vortex structures that have a dominant role in near-injector mixing and recess effects.…”

Section: Jet Structures In Recessed Injectorsmentioning

confidence: 84%

“…To understand flame stabilization, the flowfield and combustion behind the bluff body or step have been studied extensively. [17][18][19][20][21] In particular, recessing the inner post is known to be an important geometric parameter for both mixing and combustion. Practical rocket coaxial injectors typically apply a recess having a length equivalent to the inner injector diameter.…”

Section: Introductionmentioning

confidence: 99%

Effects of a Recess on Supercritical Co-Flowing Planar Jets

Muto

Terashima

Tsuboi³

2019

Trans. Japan Soc. Aero. S Sci.

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The effects of a recess on co-flowing planar jets under supercritical pressure are numerically studied. Two-dimensional hybrid LES/RANS simulations are performed in a wide range of recess lengths and injection momentum flux ratios, which are important design parameters for liquid rocket engine injectors. The present study showed that confinement effects of the near-injector flowfield by applying a recess, suppress outer jet spreading and thus enhances the penetration of the outer jet flow into the inner jet. The enhanced penetration of the outer jet flow results in the appearance of flapping motions in the inner jet. Low-frequency oscillations corresponding to the flapping motions clearly appear in the case of recessed injectors. Moreover, the confinement effects promote interactions between vortex structures resulting in vortex breakdown. Consequently, the inner-jet length is shortened, indicating an improvement in mixing when a recess is applied. The present results also show that the inner-jet length deceases as the recess length increases, and the effects of a recess remarkably appear at higher momentum flux ratios. This is explained by the vortices generated behind the post lip that is strengthened as the result of increased velocity ratio.

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“…Differences in frequency or amplitude may occur when the temperature field and the FTF in the simulation only partially match those in the experiment, but the simulation can usually be used for further investigation of the thermoacoustic mode. There are numerous studies of combustion instabilities that illustrate that LES with adiabatic walls can show a reasonable agreement with experiments: the study on a lean-premixed swirl combustor by Huang et al [8] , the LES-studies on the PRECCIN-STA configuration [9][10][11] , the massively parallel LES of a realistic helicopter combustion chamber by Wolf et al [12] , LESs of model rocket combustors (Garby et al [13] , Urbano et al [14] ) or the LESstudies of bluff-body stabilized flames by Li et al [15] and Ghani et al [16] .…”

Section: Introductionmentioning

confidence: 99%

“…• Type 1: Adiabatic walls: the majority of recent LESs simply consider the walls to be adiabatic [8][9][10][11][12][13][14][15][16][19][20][21][22] .…”

Section: Introductionmentioning

confidence: 99%

Coupling heat transfer and large eddy simulation for combustion instability prediction in a swirl burner

Kraus

Selle

Poinsot

2018

Combustion and Flame

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OATAO is an open access repository that collects the work of Toulouse researchers and makes it freely available over the web where possible. This is an author-deposited version published in : http://oatao. Large eddy simulations (LES) of combustion instabilities are often performed with simplified thermal wall boundary conditions, typically adiabatic walls. However, wall temperatures directly affect the gas temperatures and therefore the sound speed field. They also control the flame itself, its stabilization characteristics and its response to acoustic waves, changing the flame transfer functions (FTFs) of many combustion chambers. This paper presents an example of LES of turbulent flames fully coupled to a heat conduction solver providing the temperature in the combustor walls. LES results obtained with the fully coupled approach are compared to experimental data and to LES performed with adiabatic walls for a swirled turbulent methane/air burner installed at Engler-Bunte-Institute, Karlsruhe Institute of Technology and German Aerospace Center (DLR) in Stuttgart. Results show that the fully coupled approach provides reasonable wall temperature estimations and that heat conduction in the combustor walls strongly affects both the mean state and the unstable modes of the combustor. The unstable thermoacoustic mode observed experimentally at 750 Hz is captured accurately by the coupled simulation but not by the adiabatic one, suggesting that coupling LES with heat conduction solvers within combustor walls may be necessary in other configurations in order to capture flame dynamics.

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A Large-Eddy-Simulation Study of Combustion Dynamics of Bluff-Body Stabilized Flames

Cited by 35 publications

References 50 publications

MVP-Workshop Contribution: Modeling of Volvo bluff body flame experiment

MVP-Workshop Contribution: Modeling of Volvo bluff body flame experiment

Effects of a Recess on Supercritical Co-Flowing Planar Jets

Coupling heat transfer and large eddy simulation for combustion instability prediction in a swirl burner

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