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Examining the Potential of High-Order Scale-Resolving Simulation to Support RANS-Based Compressor Airfoil Optimization

Goinis, Georgios and Satcunanathan, Sutharsan and Bergmann, Michael (2025) Examining the Potential of High-Order Scale-Resolving Simulation to Support RANS-Based Compressor Airfoil Optimization. ASME Journal of Turbomachinery. American Society of Mechanical Engineers (ASME). doi: 10.1115/1.4069802. ISSN 0889-504X.

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Official URL: https://asmedigitalcollection.asme.org/turbomachinery/article/148/4/041002/1222149/Examining-the-Potential-of-High-Order-Scale

Abstract

Turbomachinery aerodynamic optimizations are predominantly carried out using Reynolds-averaged Navier–Stokes (RANS)-based computational fluid dynamics (CFD). The approach has reached a high level of maturity over the past years through extensive practical experience. With the ever-increasing demands on designs, the demands on simulation accuracy are also increasing, and efforts are being made to incorporate scale-resolving simulations (SRSs) into the design process of turbomachinery. Although SRS still remains too costly for primary use in industrial optimization, ongoing advancements favor its gradual integration. This is supported by design trends such as smaller core engines, resulting in locally reduced Reynolds numbers. Potential boundary-layer separation and a high level of unsteadiness in these low Reynolds number flows amplify the uncertainties of RANS. At the same time, the computational requirements of SRS are drastically reduced due to the reduced bandwidth of turbulent scales. To assess the potential of utilizing SRS in optimization frameworks, RANS-optimized airfoils are re-evaluated with large eddy simulations (LESs) based on a high-order discontinuous Galerkin solver. First, a RANS optimization is performed for a low Reynolds number airfoil with the aim of reducing the loss at the design point and increasing the operating range, while adhering to a constraint of nearly axial outflow angle. A subset of Pareto-front geometries is then re-simulated using LES to assess the impact of the chosen CFD methodology on the optimization result. Detailed flow analyses give insights on the deficiencies of RANS. The results demonstrate how optimizations can be driven into a sub-optimal direction when relying solely on RANS, underscoring the necessity of incorporating SRS into the process and providing initial insights into how this can be done. It is demonstrated how data obtained from only a few SRS can be fed back into the optimization process, leading to an improved optimization outcome.

Item URL in elib:https://elib.dlr.de/218548/
Document Type:Article
Additional Information:ASME permission to deposit an open copy, November 6th, 2025
Title:Examining the Potential of High-Order Scale-Resolving Simulation to Support RANS-Based Compressor Airfoil Optimization
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Goinis, GeorgiosUNSPECIFIEDhttps://orcid.org/0000-0002-1455-7673UNSPECIFIED
Satcunanathan, SutharsanUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Bergmann, MichaelUNSPECIFIEDhttps://orcid.org/0000-0003-0553-5584UNSPECIFIED
Date:23 October 2025
Journal or Publication Title:ASME Journal of Turbomachinery
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
DOI:10.1115/1.4069802
Publisher:American Society of Mechanical Engineers (ASME)
ISSN:0889-504X
Status:Published
Keywords:optimization, compressor, cascade, outlet guide vane (OGV), Reynolds-averaged Navier–Stokes (RANS), scale-resolving simulation (SRS), large eddy simulation (LES), computational fluid dynamics (CFD), turbomachinery aerodynamic design, turbomachinery blading design
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 - Virtual Engine, E - Gas Turbine
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Fan and Compressor
Institute of Propulsion Technology > Numerical Methodes
Deposited By: Goinis, Georgios
Deposited On:13 Nov 2025 18:25
Last Modified:16 Dec 2025 14:47

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