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CFD Analysis of the HyShot II scramjet combustor

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

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Official URL: Http://elsevier.com


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%.

Item URL in elib:https://elib.dlr.de/66912/
Document Type:Article
Title:CFD Analysis of the HyShot II scramjet combustor
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Fureby, C.Swedish Defense Research Agency, FOIUNSPECIFIEDUNSPECIFIED
Chapuis, M.Swedish Defense Research Agency, FOIUNSPECIFIEDUNSPECIFIED
Fedina, E.Swedish Defense Research Agency, FOIUNSPECIFIEDUNSPECIFIED
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
Volume:Vol. 33
Page Range:pp. 2399-2405
Keywords:Scramjet, HyShot II wind-tunnel experiments, Large Eddy Simulation, Supersonic mixing, Self-ignition
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):W - Grundlagen Raumtransport - numerische Verfahren (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Karl, Dr. Sebastian
Deposited On:04 Apr 2011 12:54
Last Modified:07 Feb 2013 20:41

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