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Understanding scramjet combustion using LES of the HyShot II combustor

Nordin-Bates, K. and Fureby, Christer and Karl, Sebastian and Hannemann, Klaus (2016) Understanding scramjet combustion using LES of the HyShot II combustor. Proceedings of the Combustion Institute, 36 (2), pp. 2893-2900. Elsevier. doi: 10.1016/j.proci.2016.07.118. ISSN 1540-7489.

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Official URL: https://doi.org/10.1016/j.proci.2016.07.118


Detailed understanding of the physical processes occurring in the combustor of a scramjet engine is crucial for enabling this technology and is considered the most promising for hypersonic flight. Laboratory, ground testing, and flight-testing experiments, together with simulations, comprise the tools available to fill the current gap in scramjet combustor knowledge. Here, a computational study has been carried out for the HyShot II scramjet combustor using Large Eddy Simulation (LES) models together with one skeletal and one comprehensive reaction mechanism. Based on a survey of the experimental data available for the HyShot II combustor, we focus on the High Enthalpy Shock Tunnel Göttingen (HEG) operating condition XIII, emulating flight conditions at 28 km altitude. To account for slight experimental run-to-run variations, two simulations are performed at different equivalence ratios. The LES are found to capture the experimental wall-pressure and heat-flux data well compared to the measurement data, with marginal influence of the reaction mechanism. The LES results are subsequently used to analyze the flow, mixing, and combustion processes involved. The tools employed include conventional, as well as recently developed methods, such as the Takeno flame index and Chemical Explosive Mode Analysis. These methods give a concise description of the interactions between flow, fuel–air mixing, and combustion, and it is discovered that supersonic combustion is a combination of auto-ignition and non-premixed flame regions and self-igniting fronts. Furthermore, ignition is enabled by shocks, and the supersonic flame is very different in nature to subsonic turbulent flames.

Item URL in elib:https://elib.dlr.de/109731/
Document Type:Article
Additional Information:www.elsevier.com/locate/proci Published online: 05. Oktober 2016 Computational Materials Science
Title:Understanding scramjet combustion using LES of the HyShot II combustor
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Nordin-Bates, K.Defense Security Systems Technology, Swedish Defense Research Agency –FOI, SE 147 25 Tumba, Stockholm, SwedenUNSPECIFIEDUNSPECIFIED
Fureby, ChristerDefense Security Systems Technology, Swedish Defense Research Agency –FOI, SE 147 25 Tumba, Stockholm, SwedenUNSPECIFIEDUNSPECIFIED
Karl, SebastianUNSPECIFIEDhttps://orcid.org/0000-0002-5558-6673UNSPECIFIED
Hannemann, KlausUNSPECIFIEDhttps://orcid.org/0000-0002-9653-4087UNSPECIFIED
Date:5 October 2016
Journal or Publication Title:Proceedings of the Combustion Institute
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
Page Range:pp. 2893-2900
EditorsEmailEditor's ORCID iDORCID Put Code
Series Name:Combustion science
Keywords:Supersonic combustion; Scramjet; LES; Finite-rate chemistry; Comprehensive chemistry
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Anlagen u. Messtechnik (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Bachmann, Barbara
Deposited On:04 Jan 2017 10:48
Last Modified:05 Nov 2020 18:14

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