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Scaling of Lean Aeronautical Gas Turbine Combustors

Gövert, Simon and Gruhlke, Pascal and Behrendt, Thomas and Janus, Bertram (2024) Scaling of Lean Aeronautical Gas Turbine Combustors. Journal of Engineering for Gas Turbines and Power, 146 (6). American Society of Mechanical Engineers (ASME). doi: 10.1115/1.4063776. ISSN 0742-4795.

Full text not available from this repository.

Official URL: https://dx.doi.org/10.1115/1.4063776

Abstract

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.

Item URL in elib:https://elib.dlr.de/201802/
Document Type:Article
Title:Scaling of Lean Aeronautical Gas Turbine Combustors
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Gövert, SimonUNSPECIFIEDhttps://orcid.org/0000-0003-4593-1776UNSPECIFIED
Gruhlke, PascalUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Behrendt, ThomasUNSPECIFIEDhttps://orcid.org/0000-0002-4154-3277UNSPECIFIED
Janus, BertramUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Date:4 January 2024
Journal or Publication Title:Journal of Engineering for Gas Turbines and Power
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:146
DOI:10.1115/1.4063776
Publisher:American Society of Mechanical Engineers (ASME)
ISSN:0742-4795
Status:Published
Keywords:Automated scaling, lean aeronautical gas turbine combustor, multiple operating points
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:04 Jan 2024 11:28
Last Modified:15 Jan 2024 09:16

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