Short overview on combustion systems scale‐up with emphasis on NOx emissions of gas‐fired furnaces

Drubetskoi, Eugen; Eckart, Sven; Krause, Hartmut

doi:10.1002/ese3.1028

Energy Science & Engineering

2021

DOI: 10.1002/ese3.1028

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Short overview on combustion systems scale‐up with emphasis on NOx emissions of gas‐fired furnaces

Eugen Drubetskoi

Sven Eckart

Hartmut Krause

Abstract: This is an open access article under the terms of the Creat ive Commo ns Attri bution License, which permits use, distribution and reproduction in any medium, provided the original work is properly cited.

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2024

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Cited by 2 publications

References 46 publications

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Up-scaling of a laboratory-scale pulverised oxyfuel burner to semi-industrial-scale through a flow similarity approach

Richter,

Ströhle,

Epple

2024

Fuel

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Up-scaling of a laboratory-scale pulverised oxyfuel burner to semi-industrial-scale through a flow similarity approach

Richter,

Ströhle,

Epple

2024

Fuel

View full text Add to dashboard Cite

Scaling of Lean Aeronautical Gas Turbine Combustors

Gövert,

Gruhlke,

Behrendt

et al. 2024

Journal of Engineering for Gas Turbines and Power

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A numerical procedure is presented for the scaling of lean aeronautical gas turbine combustors to different thrust classes. The procedure considers multiple operating points and aims for a self-similar flow field with respect to a reference configuration. The developed scaling approach relies on an optimization-based workflow which involves automated geometry and grid generation, unsteady Reynolds-averaged Navier-Stokes (URANS) simulations and post-processing. Kriging is applied as a meta model to identify new sets of geometrical parameters. A scaling function based on pressure loss, axial location of heat release, pilot air split and the temperature profile at the combustor exit is proposed. A generic internally-staged lean-burn high pressure aeronautical combustor has been designed to serve as a first verification test case with reactive flow characteristics comparable to real combustion chambers. The burner geometry is parameterized by 23 free parameters which are altered within the scaling process. The developed procedure is applied to scale the combustor to a lower thrust class considering multiple operating points simultaneously: take-off, approach and idle. In total, 65 different combustor variants have been evaluated within the scaling procedure. The final combustor configuration, scaled to a lower thrust class, shows good agreement to the reference configuration in terms of the scaling targets and reasonably resembles the emission indices. Integrating the scaling procedure into the design process of future combustion systems could reduce the required design iterations and thereby contribute to significantly reduced development times and costs.

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Short overview on combustion systems scale‐up with emphasis on NOx emissions of gas‐fired furnaces

Abstract: This is an open access article under the terms of the Creat ive Commo ns Attri bution License, which permits use, distribution and reproduction in any medium, provided the original work is properly cited.

Cited by 2 publications

References 46 publications

Up-scaling of a laboratory-scale pulverised oxyfuel burner to semi-industrial-scale through a flow similarity approach

Up-scaling of a laboratory-scale pulverised oxyfuel burner to semi-industrial-scale through a flow similarity approach

Scaling of Lean Aeronautical Gas Turbine Combustors

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