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The Present Challenge of Transonic Compressor Blade Design

Hergt, Alexander and Klinner, Joachim and Wellner, Jens and Willert, Christian and Grund, Sebastian and Steinert, Wolfgang and Beversdorff, Manfred (2018) The Present Challenge of Transonic Compressor Blade Design. In: Proceedings of the ASME Turbo Expo. ASME Turbo Expo, 11.06. - 15.06.2018, Oslo, Norway. doi: 10.1115/GT2018-75528.

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The flow through a transonic compressor cascade shows a very complex structure due to the occuring shock waves. In addition, the interaction of these shock waves with the blade boundary layer inherently leads to a very unsteady flow behaviour. The aim of the current investigation is to quantify this behaviour and its influence on the cascade performance as well as to describe the occuring transonic flow phenomena in detail. Therefore, an extensive experimental investigation of the flow in a transonic compressor cascade has been conducted within the transonic cascade wind tunnel of DLR at Cologne. In this process, the flow phenomena were thoroughly examined for an inflow Mach number of 1.21. The experiments investigate both, the laminar as well as the turbulent shock wave boundary layer interaction within the blade passage and the resulting unsteady behaviour. The experiments show a fluctuation range of the passage shock wave of about 10 percent chord for both cases, which is directly linked with a change of the inflow angle and of the operating point of the cascade. Thereafter, RANS simulations have been performed aiming at the verification of the reproducibility of the experimentally examined flow behavior. Here it is observed that the dominant flow effects are not reproduced by a steady numerical simulation. Therefore, a further unsteady simulation has been carried out in order to capture the unsteady flow behaviour. The results from this simulation show that the fluctuation of the passage shock wave can be reproduced but not in the correct magnitude. This leads to a remaining weak point within the design process of transonic compressor blades, because the working range will beoverpredicted. The resulting conclusion of the study is that the use of scale resolving methods such as LES or the application of DNS is necessary to correctly predict unsteadiness of the transonic cascade flow and its impact on the cascade performance.

Item URL in elib:https://elib.dlr.de/120494/
Document Type:Conference or Workshop Item (Speech)
Title:The Present Challenge of Transonic Compressor Blade Design
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Hergt, AlexanderUNSPECIFIEDhttps://orcid.org/0009-0008-1643-7326UNSPECIFIED
Klinner, JoachimUNSPECIFIEDhttps://orcid.org/0000-0003-2709-9664UNSPECIFIED
Wellner, JensUNSPECIFIEDhttps://orcid.org/0000-0003-0606-9415UNSPECIFIED
Willert, ChristianUNSPECIFIEDhttps://orcid.org/0000-0002-1668-0181UNSPECIFIED
Date:June 2018
Journal or Publication Title:Proceedings of the ASME Turbo Expo
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:Transonic, Cascade, Shock Boundary Layer Interaction
Event Title:ASME Turbo Expo
Event Location:Oslo, Norway
Event Type:international Conference
Event Dates:11.06. - 15.06.2018
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Fan and Compressor Technologies (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Fan and Compressor
Deposited By: Hergt, Dr.-Ing. Alexander
Deposited On:11 Jul 2018 09:06
Last Modified:20 Jul 2023 15:33

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