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Scaling of Lean Aeronautical Gas Turbine Combustors

Gövert, Simon and Gruhlke, Pascal and Behrendt, Thomas and Janus, Bertram (2023) Scaling of Lean Aeronautical Gas Turbine Combustors. In: ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition, GT 2023. ASME Turbo Expo 2023 Turbomachinery Technical Conference and Exposition, 2023-06-26 - 2023-06-30, Boston, MA, USA. doi: 10.1115/GT2023-101913. ISBN 978-0-7918-8695-3.

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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 numerical grid generation, unsteady Reynolds-averaged Navier-Stokes (URANS) simulations and post-processing of the reacting flow field. Kriging is applied as a meta model to identify new sets of parameters for combustor geometry generation. A generic 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 definition of a suitable scaling function is essential for the success of the scaling approach. 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. The developed procedure is tested and applied for the scaling of an internally-staged lean combustor to a lower thrust class considering multiple operating points simultaneously. In total, 65 different combustor variants have been evaluated by the scaling procedure. Simulations were performed for each of these configurations at take-off, approach and idle operating conditions. 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.

Item URL in elib:https://elib.dlr.de/196656/
Document Type:Conference or Workshop Item (Speech)
Title:Scaling of Lean Aeronautical Gas Turbine Combustors
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Gövert, SimonUNSPECIFIEDhttps://orcid.org/0000-0003-4593-1776UNSPECIFIED
Behrendt, ThomasUNSPECIFIEDhttps://orcid.org/0000-0002-4154-3277UNSPECIFIED
Journal or Publication Title:ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition, GT 2023
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:automated scaling, lean aeronautical gas turbine combustor, multiple operating points
Event Title:ASME Turbo Expo 2023 Turbomachinery Technical Conference and Exposition
Event Location:Boston, MA, USA
Event Type:international Conference
Event Start Date:26 June 2023
Event End Date:30 June 2023
Organizer:American Society of Mechanical Engineers (ASME)
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Clean Propulsion
DLR - Research area:Aeronautics
DLR - Program:L CP - Clean Propulsion
DLR - Research theme (Project):L - Components and Emissions
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Combustor
Deposited By: Gövert, Simon
Deposited On:23 Oct 2023 09:51
Last Modified:24 Apr 2024 20:56

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