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Numerical Analysis of the stability and operation of an acial compressor connected to an array of pulsed detonation combustors

Dittmar, Louise und Stathopoulos, Panagiotis (2020) Numerical Analysis of the stability and operation of an acial compressor connected to an array of pulsed detonation combustors. In: ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition, GT 2020. ASME Turbo Expo 2020 Turbomachinery Technical Conference and Exposition, 2020-09-21 - 2020-09-25, Online-Veranstaltung. doi: 10.1115/GT2020-15381. ISBN 978-079188419-5.

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Kurzfassung

Any outlet restriction downstream of Pressure Gain Combustion (PGC), such as turbine blades, affects its flow field and may cause additional thermodynamic losses. The unsteadiness in the form of pressure, temperature and velocity vector fluctuations has a negative impact on the operation of conventional turbines. Additionally, experimental measurements and data acquisition present researchers with challenges that have to do mostly with the high temperature exhaust of PGC and the high frequency of its operation. Nevertheless, numerical simulations can provide important insights into PGC exhaust flow and its interaction with turbine blades. In this paper, a Rotating Detonation Combustor (RDC) and a row of nozzle guide vanes have been modeled based on the data from literature and an available experimental setup. URANS simulations were done for five guide vane configurations with different geometrical parameters to investigate the effect of solidity and blade type representing different outlet restrictions on the RDC exhaust flow. The results analyzed the connection between total pressure loss and the vanes solidity and thickness to chord ratio. It is observed that more than 57% of the upstream velocity angle fluctuation amplitude was damped by the vanes. Furthermore, the area reduction was found to be the significant driving factor for damping the velocity angle fluctuations, whether in the form of solidity or thickness on chord ratio increment. This RDC exhaust flow investigation is an important primary step from a turbomachinery standpoint, which provided details of blade behavior in such an unsteady flow field.

elib-URL des Eintrags:https://elib.dlr.de/139741/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Numerical Analysis of the stability and operation of an acial compressor connected to an array of pulsed detonation combustors
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Dittmar, LouiseTechnical University of BerlinNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Stathopoulos, PanagiotisPanagiotis.Stathopoulos (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:2020
Erschienen in:ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition, GT 2020
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Nein
DOI:10.1115/GT2020-15381
ISBN:978-079188419-5
Status:veröffentlicht
Stichwörter:gas turbines, compressors, pressure gain combustion, 1-D CFD, stability analysis, Pulsed detonation combustion
Veranstaltungstitel:ASME Turbo Expo 2020 Turbomachinery Technical Conference and Exposition
Veranstaltungsort:Online-Veranstaltung
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:21 September 2020
Veranstaltungsende:25 September 2020
HGF - Forschungsbereich:Energie
HGF - Programm:Energieeffizienz, Materialien und Ressourcen
HGF - Programmthema:keine Zuordnung
DLR - Schwerpunkt:Energie
DLR - Forschungsgebiet:E SP - Energiespeicher
DLR - Teilgebiet (Projekt, Vorhaben):E - Dekarbonisierte Industrieprozesse (alt)
Standort: Cottbus
Institute & Einrichtungen:Institut für CO2-arme Industrieprozesse
Hinterlegt von: Klinkmüller, Maike
Hinterlegt am:04 Jan 2021 11:07
Letzte Änderung:24 Apr 2024 20:40

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