Numerical investigation into the combustion behavior of an inlet-fueled thermal-compression-like scramjet

Bricalli, Mathew G., Brown, Laurie M. and Boyce, Russell R. (2015) Numerical investigation into the combustion behavior of an inlet-fueled thermal-compression-like scramjet. AIAA Journal (American Institute of Aeronautics and Astronautics Journal), 53 7: 1740-1760. doi:10.2514/1.J053513

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Author Bricalli, Mathew G.
Brown, Laurie M.
Boyce, Russell R.
Title Numerical investigation into the combustion behavior of an inlet-fueled thermal-compression-like scramjet
Journal name AIAA Journal (American Institute of Aeronautics and Astronautics Journal)   Check publisher's open access policy
ISSN 0001-1452
1533-385X
Publication date 2015-07
Year available 2015
Sub-type Article (original research)
DOI 10.2514/1.J053513
Open Access Status File (Author Post-print)
Volume 53
Issue 7
Start page 1740
End page 1760
Total pages 21
Place of publication Reston, VA United States
Publisher American Institute of Aeronautics and Astronautics
Collection year 2016
Language eng
Abstract A numerical study on the combustion behavior of an inlet-fueled three-dimensional nonuniform-compression scramjet is presented. This paper is an extension to previous work on the combustion processes in a premixed three-dimensional nonuniform-compression scramjet, where thermal compression was shown to enhance combustion. This paper demonstrates how thermal compression can be used in a generic scramjet configuration with a realistic fuel-injection method to enhance performance at high flight Mach numbers. Such a scramjet offers an extra degree of freedom in the design process of fixed-geometry scramjets that must operate over a range of flight Mach numbers. In this study, how the combustion processes are affected is investigated, with the added realism of inlet porthole fuel injection. Ignition is established from within a shock-induced boundary-layer separation at the entrance to the combustor. Radicals that form upstream of the combustor within the inlet, from the injection method, enhance combustion. Coupling of the inlet-induced spanwise gradients and thermal compression improves combustion. The results highlight that, although the fuel-injection method imparts local changes to the flow structures, the global flow behavior does not change compared to previous premixed results. This combustion behavior will be reproduced when using other fueling methods that deliver partially premixed fuel and air to the combustor entrance.
Keyword Supersonic combustion
Scramjets
Thermal compression
Nonuniform compression
Computational fluid dynamics (CFD)
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 2016 Collection
 
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Created: Wed, 11 Mar 2015, 15:02:43 EST by Matthew Bricalli on behalf of Faculty Of Engineering, Architecture & Info Tech