Large Eddy Simulation of the PRECCINSTA burner

Wang, P.; Platova, N.; Fröhlich, Jochen; Maas, U.

doi:10.1016/j.ijheatmasstransfer.2013.11.025

Cited by 30 publications

(18 citation statements)

References 30 publications

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“…The double peak appearing in Fig. 8 at upstream locations is consistent with LES in literature (Benard, 2018;Ansari, 2014;Wang, 2014). The RMS values for the mass fractions are consistently slightly underpredicted, particularly at locations downstream of 20 mm and, in the case of H2O and CO2, in the outer flame region.…”

Section: Resultssupporting

confidence: 88%

“…To this end, the DQMoM model is validated in the framework of LES for the swirl-stabilised PRECCINSTA model gas turbine combustor (Meier et al, 2007). In order to quantify the accuracy of the DQMoM approach for this complex test case, comparisons are made to both experiment and further LES data, since a large number of studies using this combustor are present in the literature (Franzelli et al, 2012;Ansari et al, 2014;Wang et al, 2014;Benard et al, 2018;Fredrich et al, 2019;Verma et al, 2019).…”

Section: Introductionmentioning

confidence: 99%

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Numerical Investigation of Swirl-Stabilised Model Gas Turbine Combustor using DQMoM with LES

Emmi¹,

Fiolitakis²,

Aigner³

2020

Proceedings of Global Power &Amp; Propulsion Society

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A detailed numerical investigation of the swirling reactive flow in the PRECCINSTA model burner for gas turbines is carried out using the Direct Quadrature Method of Moments (DQMoM) in the context of Large Eddy Simulation (LES). DQMoM is used in this work to solve the filtered transport equations of the one-time, one-point joint thermochemical probability density function (PDF) for species and enthalpy. Transported PDF methods offer the invaluable advantage of a closed chemical source term, while DQMoM in particular provides a method for solving the PDF transport equations at reasonable computational costs: a highly valuable advantage for large, complex burners. Previous studies have examined this particular burner using LES and variety of sub-grid combustion models, chiefly with a focus on unsteady thermoacoustic modes and corresponding flow phenomena. In this work, the emphasis is placed on the flow phenomena in the stable mode, with the use of detailed chemistry due to the computational efficiency offered by DQMoM. The results are critically analysed and compared with the available experimental as well as LES model results, highlighting the particular usefulness of the DQMoM approach in the context of LES for complex burners.

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Section: Resultssupporting

confidence: 88%

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Swirl-Stabilised Model Gas Turbine Combustor using DQMoM with LES

Emmi¹,

Fiolitakis²,

Aigner³

2020

Proceedings of Global Power &Amp; Propulsion Society

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“…The PRECCINSTA combustor has been analyzed numerically in several previous studies [11,17,18,19,20,6,21,22]. Most of these works [11,17,18,19,20,22], however, investigated either stable operating conditions or assumed a perfectly premixed flame. For the same combustor and operating condition as in this work, the frequency of the thermoacoustic oscillation was computed in an LES by Franzelli et al with a discrepancy of 100 Hz to the measured data [6].…”

Section: Introductionmentioning

confidence: 99%

Scale Adaptive Simulation of a thermoacoustic instability in a partially premixed lean swirl combustor

Lourier

Stöhr

Noll

et al. 2017

Combustion and Flame

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The thermoacoustic oscillation of a turbulent, swirl-stabilized, partially premixed flame in the PRECCINSTA gas turbine model combustor is analyzed by means of a Scale Adaptive Simulation (SAS) method. In the critical regions of the combustor the SAS features a fine spatial resolution and thus corresponds to a Large Eddy Simulation (LES). Two combustion models are applied, a simple eddy dissipation model and a detailed finite rate chemistry (FRC) model. A previous LES for the same combustor by Franzelli et al. [Combust. Flame 159 (2012) 621-637] indicated that the acoustic impedance of the fuel supply plays a critical role. Therefore in the present work, the fuel channels and fuel plenum are included in the computational domain and thereby the fuel inlet impedance is inherently taken into account. The resulting fields of velocity, temperature and mixture fraction fit well to experimental data with a slightly better agreement for the detailed FRC model. For both combustion models the computed frequency of the thermoacoustic oscillation is close to the experimental value, whereas its amplitude is significantly overestimated by about 15 dB in comparison to measurements. The reason for this overestimation is analyzed using an additional measurement where acoustic damping due to vibrating side walls is suppressed. For the latter experiment both frequency and amplitude agree well with CFD results, which indicates that acoustic damping effects must be carefully taken into account for validation of CFD. The 3D time-resolved simulations further provide detailed insights into the interaction of flow and mixing in the swirler, which leads to a convective time-lag between oscillations of velocity and equivalence ratio in the flow of unburned gas that largely affects the heat release response of the flame. Taken together, the results show that SAS computations can accurately reproduce frequency and amplitude of thermoacoustic oscillations of turbulent partially premixed flames in a gas turbine combustor provided that proper modeling of fuel supply and acoustic boundary conditions is applied.

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“…The test case corresponds to a gas turbine model combustor that has been experimentally investigated at the German Aerospace Center (DLR) by Meier et al [ 4 ]. The combustor has been used extensively as a test case for modeling validation [ 5 – 16 ], while other authors were focused on the description of the flow field and combustion dynamics by means of numerical simulations [ 17 – 20 ]. In the majority of the modeling attempts, perfectly premixing is assumed in order to apply premixed turbulent combustion models.…”

Section: Introductionmentioning

confidence: 99%

The Effect of Partial Premixing and Heat Loss on the Reacting Flow Field Prediction of a Swirl Stabilized Gas Turbine Model Combustor

Gövert

Mira

Kok

et al. 2017

Flow Turbulence Combust

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This work addresses the prediction of the reacting flow field in a swirl stabilized gas turbine model combustor using large-eddy simulation. The modeling of the combustion chemistry is based on laminar premixed flamelets and the effect of turbulence-chemistry interaction is considered by a presumed shape probability density function. The prediction capabilities of the presented combustion model for perfectly premixed and partially premixed conditions are demonstrated. The effect of partial premixing for the prediction of the reacting flow field is assessed by comparison of a perfectly premixed and partially premixed simulation. Even though significant mixture fraction fluctuations are observed, only small impact of the non-perfect premixing is found on the flow field and flame dynamics. Subsequently, the effect of heat loss to the walls is assessed assuming perfectly premixing. The adiabatic baseline case is compared to heat loss simulations with adiabatic and non-adiabatic chemistry tabulation. The results highlight the importance of considering the effect of heat loss on the chemical kinetics for an accurate prediction of the flow features. Both heat loss simulations significantly improve the temperature prediction, but the non-adiabatic chemistry tabulation is required to accurately capture the chemical composition in the reacting layers.

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Large Eddy Simulation of the PRECCINSTA burner

Cited by 30 publications

References 30 publications

Numerical Investigation of Swirl-Stabilised Model Gas Turbine Combustor using DQMoM with LES

Numerical Investigation of Swirl-Stabilised Model Gas Turbine Combustor using DQMoM with LES

Scale Adaptive Simulation of a thermoacoustic instability in a partially premixed lean swirl combustor

The Effect of Partial Premixing and Heat Loss on the Reacting Flow Field Prediction of a Swirl Stabilized Gas Turbine Model Combustor

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