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Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor: Part I: Shock-tunnel experiments

Laurence, Stuart Jon and Lieber, Damien and Martinez Schramm, Jan and Hannemann, Klaus and Larsson, Johan (2015) Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor: Part I: Shock-tunnel experiments. Combustion and Flame, 162 (4), pp. 921-931. Elsevier. DOI: 10.1016/j.combustflame2014.09016 ISSN 0010-2180

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Official URL: http://www.sciencedirect.com/science/article/pii/S0010218014002971

Abstract

A series of experiments is performed in the High Enthalpy ShockTunnel Göttingen to investigate the response of the HyShotII scramjet combustor to equivalence ratios close to the critical value at which the onset of thermal choking occurs. This critical equivalence ratio is first identified (for simulated Mach-8, 27-km altitude conditions) as 0.38-0.39. Subsequent experiments cover the range between this value and 0.50. As the HyShotII combustor has a constant-area cross section, the expected behavior in this equivalence-ratio range is the formation and upstream propagation of an unsteady shock train, that would eventually lead to inlet unstart. Instead, however, the shock train is observed to become lodged in the in the heat-release zone of the combustion chamber, with a quasi-stable position that shifts upstream within creasing equivalence ratio. This behavior is distinct from the steady isolator shock train is observed to become lodged in the heat-release zone of the combustion chamber, with a quasi-stable position that shifts upstream with increasing equivalence ratio. This behavior is distinct from the steady isolator shock trains seen in traditional dual-mode scramjet configurations. The shock-train development in the present experiments is characterized through fast-response surface pressure and heat-flux measurements, as well as simultaneous high-speed schlieren and OH*chemiluminescence visualization. Possible explanations for this unexpected behavior are proposed in terms of the increased heat-transfer to the combustor walls and a possible increased uniformity of the heat release across the combustor cross-section caused by the presence of the shock train.

Item URL in elib:https://elib.dlr.de/89193/
Document Type:Article
Additional Information:Published online: 08. Oct. 2014, April 2015
Title:Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor: Part I: Shock-tunnel experiments
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Laurence, Stuart Jonstuart.laurence (at) dlr.deUNSPECIFIED
Lieber, Damiendamien.lieber (at) dlr.deUNSPECIFIED
Martinez Schramm, Janjan.martinez (at) dlr.deUNSPECIFIED
Hannemann, Klausklaus.hannemann (at) dlr.deUNSPECIFIED
Larsson, JohanbDepartment of Mechanical Engineering, University of Maryland, College Park, MD 20742, USAUNSPECIFIED
Date:2015
Journal or Publication Title:Combustion and Flame
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:162
DOI :10.1016/j.combustflame2014.09016
Page Range:pp. 921-931
Publisher:Elsevier
ISSN:0010-2180
Status:Published
Keywords:stable shock-train formation, scramjet combustor, Shock-tunnel experiments
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Numerische Verfahren und Simulation
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Micknaus, Ilka
Deposited On:08 Dec 2014 12:39
Last Modified:10 Jan 2019 15:46

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