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UNSTEADY FULL ANNULUS MULTI-STAGE COMPRESSOR CALCULATIONS - DETAILS ON CFD-EXPERIMENT COMPARISON

Reutter, Oliver and Ashcroft, Graham and Nicke, Eberhard and Kügeler, Edmund (2017) UNSTEADY FULL ANNULUS MULTI-STAGE COMPRESSOR CALCULATIONS - DETAILS ON CFD-EXPERIMENT COMPARISON. In: 4th AIAA/CEAS Aeroacoustics Conference. 6TH CEAS AIR & SPACE CONFERENCE AEROSPACE EUROPE 2017, 16.-20. Oktober 2017, Rumänien, Bukarest.

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Abstract

The unsteady flow in a multi-stage compressor has been simulated using time-domain methods to gain a better insight into the complex flow physics and address the computational bottlenecks associated with large scale numerical simulations in the time domain. For these investigations the time-periodic flow in the DLR research compressor Rig250 has been simulated. Rig250 is a 4.5 stage axial flow compressor with a swan neck that includes struts for support. In the time-domain simulation the struts, IGVs and first two stages are computed time-accurately using a full annulus mesh to fully capture the blade row interactions. The remaining two stages are included in the simulation by solving, with single passages, for the time-mean flow. In total, the low Reynolds full annulus mesh comprises nearly 1 billion nodes distributed over 6000 blocks. For an operating point close to maximum efficiency, comparisons are made between the time-accurate full annulus calculation and experimental test data to see how Kiel probe stagnation pressure measurements can be resolved. It is shown, that with larger efforts in simulations also the comparison between numerical and experimental data has to be conducted with greater care. The numerical and experimental results are in good agreement.The unsteady flow in a multi-stage compressor has been simulated using time-domain methods to gain a better insight into the complex flow physics and address the computational bottlenecks associated with large scale numerical simulations in the time domain. For these investigations the time-periodic flow in the DLR research compressor Rig250 has been simulated. Rig250 is a 4.5 stage axial flow compressor with a swan neck that includes struts for support. In the time-domain simulation the struts, IGVs and first two stages are computed time-accurately using a full annulus mesh to fully capture the blade row interactions. The remaining two stages are included in the simulation by solving, with single passages, for the time-mean flow. In total, the low Reynolds full annulus mesh comprises nearly 1x109 nodes distributed over 6000 blocks. For an operating point close to maximum efficiency, comparisons are made between the time-accurate full annulus calculation and experimental test data to see how Kiel probe stagnation pressure measurements can be resolved. It is shown, that with larger efforts in simulations also the comparison between numerical and experimental data has to be conducted with greater care. The numerical and experimental results are in good agreement.

Item URL in elib:https://elib.dlr.de/116533/
Document Type:Conference or Workshop Item (Speech)
Title:UNSTEADY FULL ANNULUS MULTI-STAGE COMPRESSOR CALCULATIONS - DETAILS ON CFD-EXPERIMENT COMPARISON
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Reutter, Oliveroliver.reutter (at) dlr.deUNSPECIFIED
Ashcroft, Grahamgraham.ashcroft (at) dlr.deUNSPECIFIED
Nicke, Eberhardeberhard.nicke (at) dlr.deUNSPECIFIED
Kügeler, Edmundedmund.kuegeler (at) dlr.deUNSPECIFIED
Date:19 October 2017
Journal or Publication Title:4th AIAA/CEAS Aeroacoustics Conference
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
Status:Published
Keywords:CFD, Turbomachinery, Full annulus
Event Title:6TH CEAS AIR & SPACE CONFERENCE AEROSPACE EUROPE 2017
Event Location:Rumänien, Bukarest
Event Type:international Conference
Event Dates:16.-20. Oktober 2017
Organizer:Council of European Aerospace Societies
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
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Fan and Compressor
Deposited By: Reutter, Oliver
Deposited On:14 Dec 2017 09:39
Last Modified:13 Feb 2018 13:20

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