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Measuring the velocity field of a shear-coaxial, cryogenic flame in a high-pressure rocket thrust chamber

Son, Min und Armbruster, Wolfgang und Hardi, Justin und Oschwald, Michael (2020) Measuring the velocity field of a shear-coaxial, cryogenic flame in a high-pressure rocket thrust chamber. Proceedings of the Combustion Institute, 38 (2), 3389 - 3397. Elsevier. doi: 10.1016/j.proci.2020.07.076. ISSN 1540-7489.

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Kurzfassung

High-speed imaging was used to visualize one of the transcritical flames in a multi-injector, sub-scale rocket thrust chamber at pressures up to 80 bar. Image correlation velocimetry (ICV) was applied to the imaging to obtain quantitative information on the flow field from the shear-coaxial injectors. ICV was used to track surface irregularities on the liquid oxygen (LOX) jet in imaging filtered to blue wavelengths. By choosing the interrogation area carefully, only the LOX jet was effectively tracked, excluding the coaxial H2 flow, and the time-averaged velocity field was reconstructed. Due to the transient nature of the tracked features, which frequently change shape or disappear, the averaged ICV result underestimates the absolute values of velocity. Therefore, the averaged values were scaled by the mean of the instantaneous velocity maxima. A second, reference measurement of LOX jet propagation speed was calculated using dynamic mode decomposition (DMD). The results were consistent following the aforementioned correction of the ICV values. Comparing the ICV fields for two different operating conditions showed a marked difference in the axial velocity distribution and lateral expansion of the LOX jet, demonstrating the potential of the method in studying injection in rocket combustion chambers.

elib-URL des Eintrags:https://elib.dlr.de/145846/
Dokumentart:Zeitschriftenbeitrag
Titel:Measuring the velocity field of a shear-coaxial, cryogenic flame in a high-pressure rocket thrust chamber
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Son, MinMin.Son (at) dlr.dehttps://orcid.org/0000-0003-3182-0637NICHT SPEZIFIZIERT
Armbruster, WolfgangWolfgang.Armbruster (at) dlr.dehttps://orcid.org/0000-0002-4859-4173148017728
Hardi, JustinJustin.Hardi (at) dlr.dehttps://orcid.org/0000-0003-3258-5261NICHT SPEZIFIZIERT
Oschwald, MichaelMichael.Oschwald (at) dlr.dehttps://orcid.org/0000-0002-9579-9825NICHT SPEZIFIZIERT
Datum:19 September 2020
Erschienen in:Proceedings of the Combustion Institute
Referierte Publikation:Ja
Open Access:Ja
Gold Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Ja
Band:38
DOI:10.1016/j.proci.2020.07.076
Seitenbereich:3389 - 3397
Verlag:Elsevier
ISSN:1540-7489
Status:veröffentlicht
Stichwörter:liquid rocket engine, transcritical injection, flame visualization, image correlation velocimetry
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Raumtransport
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):R - Wiederverwendbare Raumfahrtsysteme und Antriebstechnologie
Standort: Lampoldshausen
Institute & Einrichtungen:Institut für Raumfahrtantriebe > Raketenantriebstechnologie
Hinterlegt von: Hanke, Michaela
Hinterlegt am:22 Nov 2021 08:36
Letzte Änderung:04 Dez 2023 12:23

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