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Some Aspects of Transonic Compressor Tandem Design

Hergt, Alexander and Siller, Ulrich and Grund, Sebastian and Klinner, Joachim and Steinert, Wolfgang and Beversdorff, Manfred (2018) Some Aspects of Transonic Compressor Tandem Design. In: Proceedings of the ASME Turbo Expo. ASME Turbo Expo, 11.06. - 15.06.2018, Oslo, Norway. doi: 10.1115/GT2018-75132.

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The development of modern axial compressors has already reached a high level. Therefore an enlargement of the design space by means of new or advanced aerodynamic methods is necessary in order to achieve further enhancements of performance and efficiency. The tandem arrangement of profiles in a transonic compressor blade row is such a method. It is necessary to address the design aspects a bit more in detail in order to efficiently apply this blading concept to turbomachinery. Therefore, in the current study the known design aspects of tandem blading in compressors will be summed up under consideration of the aerodynamic effects and construction characteristics of a transonic compressor tandem. Based on this knowledge, a new transonic compressor tandem cascade (DLR TTC) with an inflow Mach number of 0.9 is designed using modern numerical methods and a multi objective optimization process. Three objective functions as well as three operating points are used in the optimization. Furthermore, both tandem blades and their arrangement are parameterized. From the resulting database of 1246 members a final best member is chosen as state-of-the-art design for further detailed investigation. The aim of the ensuing experimental and numerical investigation is to answer the question, whether the tandem cascade resulting from the modern design process fulfills the described design aspects and delivers the requested performance and efficiency criteria. The numerical simulations within the study are carried out with the DLR flow solver TRACE. The experiments are performed at the Transonic Cascade Wind Tunnel of DLR in Cologne. The inflow Mach number during the tests is 0.9 and the AVDR [1, 2] is adjusted to 1.3 (design value). Wake measurements with a 3-hole probe are carried out in order to determine the cascade performance. The experimental results show an increase in losses and a reduction of the cascade deflection by about 2 degrees compared to design concept. Nevertheless, the experimental and numerical results allow a good understanding of the aerodynamic effects. In addition, Planar PIV was applied in a single S1 plane located at midspan to capture the velocity field in the wake of blade 1 in order to analyze the wake flow in detail and describe its influence on the cascade deflection and loss behavior. Finally, an outlook will be given on what future tandem compressor research should be focused.

Item URL in elib:https://elib.dlr.de/120495/
Document Type:Conference or Workshop Item (Speech)
Title:Some Aspects of Transonic Compressor Tandem 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
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 Tandem Compressor, Optimization, Design
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 09:07
Last Modified:20 Jul 2023 15:33

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