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Automated aerodynamic optimization of an aggressive s-shaped intermediate compressor duct

Stürzebecher, Thomas und Goinis, Georgios und Voss, Christian und Sahota, Harsimar und Groth, Pieter und Hammer, Steffen (2018) Automated aerodynamic optimization of an aggressive s-shaped intermediate compressor duct. In: Proceedings of the ASME Turbo Expo. American Society of Mechanical Engineers. ASME Turbo Expo 2018: Turbomachinery Technical Conference & Exposition, 2018-06-11 - 2018-06-15, Lillestrøm (Oslo), Norway. doi: 10.1115/GT2018-75184.

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Kurzfassung

As bypass-ratio in modern aero engines is continuously increasing over the last decades, the radial offset between low pressure compressor (LPC) and high pressure compressor (HPC), which needs to be overcome by the connecting s-shaped intermediate compressor duct (ICD), is getting higher. Due to performance and weight saving aspects the design of shorter and therefore more aggressive ducts has become an important research topic. In this paper an already aggressive design (with respect to current aero engines) of an ICD with integrated outlet guide vane (OGV) is used as a baseline for an aerodynamic optimization. The aim is to shorten the duct even further while maintaining it separation free. The optimization is broken down into two steps. In the first optimization-step the baseline design is shortened to a feasible extent while keeping weak aerodynamic restrictions. The resulting highly aggressive duct (intermediate design), which is shortened by 19 % in axial length with respect to the baseline, shows separation tendencies of low momentum fluid in the strut/hub region. For the second step, the length of the optimized duct design is frozen. By implementing new design features in the process of the optimizer, this optimization-step aims to eliminate separation and to reduce separation tendencies caused by the aggressive shortening. In particular, these features are: a nonaxisymmetric endwall contouring and parametrization of the strut and the OGV to allow for changes in lift and turning in both blade designs. By comparison of the three designs: Baseline, intermediate (separating flow) and final design, it can be shown, that it is possible to decrease length of the already aggressive baseline design even further, when adding a nonaxisymmetric endwall contouring and changes in blade shape of the strut and OGV. Flow separation can be eliminated while losses are kept low. With a more aggressive and therefore shorter duct the engine length and weight can be reduced. This in turn leads to lighter aircrafts, less fuel consumption and lower CO2 and NOx emissions.

elib-URL des Eintrags:https://elib.dlr.de/143515/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Automated aerodynamic optimization of an aggressive s-shaped intermediate compressor duct
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Stürzebecher, Thomasthomas.stuerzebecher (at) dlr.dehttps://orcid.org/0000-0001-9679-5124NICHT SPEZIFIZIERT
Goinis, GeorgiosGeorgios.Goinis (at) dlr.dehttps://orcid.org/0000-0002-1455-7673NICHT SPEZIFIZIERT
Voss, Christianchristian.voss (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Sahota, HarsimarMTUNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Groth, PieterGKNNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Hammer, SteffenGKNNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:Juni 2018
Erschienen in:Proceedings of the ASME Turbo Expo
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Nein
DOI:10.1115/GT2018-75184
Verlag:American Society of Mechanical Engineers
Status:veröffentlicht
Stichwörter:inter compressor duct, s-duct, aerodynamic optimization, axial compressor
Veranstaltungstitel:ASME Turbo Expo 2018: Turbomachinery Technical Conference & Exposition
Veranstaltungsort:Lillestrøm (Oslo), Norway
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:11 Juni 2018
Veranstaltungsende:15 Juni 2018
Veranstalter :ASME International Gas Turbine Institute
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Luftfahrt
HGF - Programmthema:Antriebssysteme
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L ER - Engine Research
DLR - Teilgebiet (Projekt, Vorhaben):L - Verdichtertechnologien (alt)
Standort: Köln-Porz
Institute & Einrichtungen:Institut für Antriebstechnik > Fan- und Verdichter
Hinterlegt von: Dygutsch, Thomas
Hinterlegt am:19 Aug 2021 07:49
Letzte Änderung:24 Apr 2024 20:43

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