Modal decomposition of the unsteady non-reactive flow field in a swirl-stabilized combustor operated by a Lean Premixed injection system

Salvador, F.J.; Carreres, Marcos; García-Tíscar, J.; Belmar-Gil, M.

doi:10.1016/j.ast.2021.106622

Cited by 19 publications

(2 citation statements)

References 62 publications

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“…29 In this study, n-decane (10 carbon atoms) is chosen as a diesel representative fuel surrogate at the desired operating condition together with the specified laminar burning velocity. The local equivalence ratio is defined based on the mixture fraction as shown in equation (13). A beta function correlation based on maximum burning velocity S max 0 and the corresponding equivalence ratio φ max is used to model the burning velocity decay to zero at the fuel-lean φ l and fuel-rich φ r flammability limits as shown in equations ( 14) and (15).…”

Section: Numerical Setupmentioning

confidence: 99%

“…The analysis of LES results has garnered significant attention in recent years with emphasis on investigating flow patterns within similar swirl burners in a variety of configurations using proper orthogonal decomposition (POD). [13][14][15] These exemplary investigations, however, typically focus on premixed combustion and highlight some difficulties and limitations of this approach. Firstly, performing POD on such LES results requires significant computational resources and manual intervention to consider many variables within the flow field that might be relevant to the investigation.…”

Section: Introductionmentioning

confidence: 99%

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Combustion dynamics analysis of a pressurized airblast swirl burner using proper orthogonal decomposition

Ghasemi,

Christou,

Kok

et al. 2023

International Journal of Spray and Combustion Dynamics

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Jet fuel-fired combustors in aero gas turbine engines have switched to lean burn to decrease nitric oxide emissions in recent years as a result of strict emission regulations. Lean operating conditions, however, exhibit a heightened sensitivity to thermoacoustic instabilities and such burners require careful consideration in design and operation. Similar to natural gas-fired combustors, they exhibit thermoacoustic instabilities, but the characteristics are more complex and less well-studied. This paper presents a numerical investigation of an airblast jet fuel swirl burner operating with preheated air at lean pressurized conditions. In order to understand the acoustic characteristics of the in-house designed burner (Magister UT burner), detached eddy simulations are performed at relevant aero engine conditions. Simulation results are then analyzed by means of our internally developed parallel modal analysis package, PARAMOUNT, to perform proper orthogonal decomposition (POD) on large datasets. The resulting modes are inspected to highlight flow features of interest and their associated acoustic frequencies at unforced conditions. Single frequency acoustic forcing is employed to study the acoustic response of the burner to perturbations at similar frequencies to its precessing vortex core. We show that parallel computation of POD modes is a viable tool to investigate the main flow features of swirl burners and is suitable for highlighting the important acoustic frequencies without the need to employ fully compressible computational fluid dynamics solvers. Additionally, the analysis method reveals the ways in which various flow structures correlate with each other and how external perturbations modify them.

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Section: Numerical Setupmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%