Supersonic boundary-layer combustion: Effects of upstream entropy and shear-layer thickness

Kirchhartz, RM, Mee, DJ, Stalker, RJ, Jacobs, PA and Smart, MK (2010) Supersonic boundary-layer combustion: Effects of upstream entropy and shear-layer thickness. Journal of Propulsion and Power, 26 1: 57-66. doi:10.2514/1.44485

Author Kirchhartz, RM
Mee, DJ
Stalker, RJ
Jacobs, PA
Smart, MK
Title Supersonic boundary-layer combustion: Effects of upstream entropy and shear-layer thickness
Journal name Journal of Propulsion and Power   Check publisher's open access policy
ISSN 0748-4658
ISBN 0748-4658; 1533-3876
Publication date 2010-01-01
Sub-type Article (original research)
DOI 10.2514/1.44485
Volume 26
Issue 1
Start page 57
End page 66
Total pages 10
Place of publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Language eng
Formatted abstract
There is much interest in the way in which fuel is injected into scramjet combustors and the way this influences ignition and combustion. Experiments were conducted in the T4 Stalker Tube to assess the combustion of hydrogen when it is injected directly into the boundary layer of a circular constant-area supersonic combustion chamber (M > 4). The wall-layer conditions at the fuel-injection station were varied to study the effects on the ignition and combustion of the injected hydrogen. This was achieved by varying the leading-edge bluntness and the length of the constant-area inlet upstream of the annular fuel-injection slot that delivers fuel as a layer underneath the existing boundary layer. Flow properties at the injection location calculated using computational fluid dynamics are presented as well as experimental data and analytical predictions of the pressure distributions along the combustion chamber wall. It is shown that a thicker boundary layer promotes combustion and that leading-edge bluntness, which leads to more hot gas near the walls, is more effective for ignition.
© Copyright 2011 American Institute of Aeronautics and Astronautics, Inc.
Keyword Boundary layers
Combustion chambers
Computational fluid dynamics
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2011 Collection
Version Filter Type
Citation counts: TR Web of Science Citation Count  Cited 5 times in Thomson Reuters Web of Science Article | Citations
Scopus Citation Count Cited 8 times in Scopus Article | Citations
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Created: Sun, 07 Feb 2010, 10:02:56 EST