elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Impressum | Kontakt | English
Schriftgröße: [-] Text [+]

CFD Analysis of the HyShot II scramjet combustor

Fureby, C. und Chapuis, M. und Fedina, E. und Karl, Sebastian (2011) CFD Analysis of the HyShot II scramjet combustor. Proceedings of the Combustion Institute, Vol. 33 (2), Seiten 2399-2405. Elsevier. DOI: 10.1016/j.proci.2010.07.055. ISSN 1540-7889.

Dieses Archiv kann nicht den gesamten Text zur Verfügung stellen.

Offizielle URL: Http://elsevier.com

Kurzfassung

The development of novel air-breathing engines such as supersonic combustion ramjets (scramjets) depends on the understanding of upersonic mixing, self-ignition and combustion. These aerothermochemical processes occur together in a scramjet engine and are notoriously difficult to understand. In the present study, we aim at analyzing the HyShot II scramjet combustor mounted in the High Enthalpy Shock Tunnel Goettingen (HEG) by using Reynolds Averaged Navier Stokes (RANS) and Large Eddy Simulation (LES) models with detailed and reduced chemistry. To account for the complicated flow in the HEG facility a zonal approach is adopted in which RANS is used to simulate the flow in the HEG nozzle and test-section, providing the necessary inflow boundary conditions for more detailed RANS and LES of the reacting flow in the HyShot combustor. Comparison of predicted wall pressures and heat fluxes with experimental data show good agreement, and in particular does the LES agree well with the experimental data. The LES results are used to elucidate the flow, mixing, self-ignition and subsequent combustion processes in the combustor. The combustor flow can be separated into the mixing zone, in which turbulent mixing from the jet-in-cross flow injectors dominates, the self-ignition zone, in which self-ignition rapidly takes place, and the turbulent combustion zone, located towards the end of the combustor, in which most of the heat release and volumetric expansion takes place. Self-ignition occurs at some distance downstream of the injectors, resulting in a distinct pressure rise further downstream due to the volumetric expansion as observed in the experiments. The jet penetration is about 30% of the combustor height and the combustion efficiency is found to be around 83%.

Dokumentart:Zeitschriftenbeitrag
Titel:CFD Analysis of the HyShot II scramjet combustor
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
Fureby, C.Swedish Defense Research Agency, FOI
Chapuis, M.Swedish Defense Research Agency, FOI
Fedina, E.Swedish Defense Research Agency, FOI
Karl, SebastianNICHT SPEZIFIZIERT
Datum:2011
Erschienen in:Proceedings of the Combustion Institute
Referierte Publikation:Ja
In Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Ja
Band:Vol. 33
DOI :10.1016/j.proci.2010.07.055
Seitenbereich:Seiten 2399-2405
Verlag:Elsevier
ISSN:1540-7889
Status:veröffentlicht
Stichwörter:Scramjet, HyShot II wind-tunnel experiments, Large Eddy Simulation, Supersonic mixing, Self-ignition
HGF - Forschungsbereich:Verkehr und Weltraum (alt)
HGF - Programm:Weltraum (alt)
HGF - Programmthema:W RP - Raumtransport
DLR - Schwerpunkt:Weltraum
DLR - Forschungsgebiet:W RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):W - Grundlagen Raumtransport - numerische Verfahren (alt)
Standort: Göttingen
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Raumfahrzeuge
Hinterlegt von: Sebastian Karl
Hinterlegt am:04 Apr 2011 12:54
Letzte Änderung:07 Feb 2013 20:41

Nur für Mitarbeiter des Archivs: Kontrollseite des Eintrags

Blättern
Suchen
Hilfe & Kontakt
Informationen
electronic library verwendet EPrints 3.3.12
Copyright © 2008-2013 Deutsches Zentrum für Luft- und Raumfahrt (DLR). Alle Rechte vorbehalten.