Supersonic Combustion Processes in a Premixed Three-Dimensional Nonuniform-Compression Scramjet Engine

Bricalli, Mathew G., Brown, Laurie M. and Boyce, Russell R. (2014) Supersonic Combustion Processes in a Premixed Three-Dimensional Nonuniform-Compression Scramjet Engine. AIAA Journal, 52 8: 1670-1685. doi:10.2514/1.J052640


Author Bricalli, Mathew G.
Brown, Laurie M.
Boyce, Russell R.
Title Supersonic Combustion Processes in a Premixed Three-Dimensional Nonuniform-Compression Scramjet Engine
Journal name AIAA Journal   Check publisher's open access policy
ISSN 0001-1452
1533-385X
Publication date 2014-08-28
Year available 2014
Sub-type Article (original research)
DOI 10.2514/1.J052640
Open Access Status
Volume 52
Issue 8
Start page 1670
End page 1685
Total pages 16
Place of publication Reston, VA United States
Publisher American Institute of Aeronautics and Astronautics
Collection year 2015
Language eng
Formatted abstract
A numerical study was undertaken using the commercial computational-fluid-dynamics code CFD++ to analyze the combustion behavior of a three-dimensional nonuniform-compression scramjet. Work here was inspired by Ferri’s concept of thermal compression and extended this to include the influence of three-dimensional viscous flow phenomena on the combustion behavior. A premixed H2/air mixture with an equivalence ratio of 1 was used to eliminate the influence of the fuel-injection method on the combustion characteristics. The freestream properties corresponded to a Mach 10 flight condition that gave a flow enthalpy, total temperature, and total pressure of 4.5  MJ/kg, 4676 K, and 29 MPa, respectively. The combustion flame was found to propagate throughout the entire bottom wall of the combustor. Three flame propagation processes were identified: three-dimensional flow structures that provide ignition sources within the boundary layer, radical transport within a three-dimensional shock-induced boundary-layer separation, and thermal compression due to combustion within the high compression region. The investigation successfully characterises each individual flame propagation mechanism on the flowfield. The results highlight the closely coupled interaction between the fluid dynamic and combustion processes within a three-dimensional scramjet engine, which offers insight into how these mechanisms can be exploited to provide superior scramjet performance over a range of flight Mach numbers.
Keyword Supersonic combustion
Thermal compression
Nonuniform compression
Airbreathing propulsion
Scramjet
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 2015 Collection
 
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Citation counts: TR Web of Science Citation Count  Cited 2 times in Thomson Reuters Web of Science Article | Citations
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Created: Wed, 11 Mar 2015, 14:57:33 EST by Matthew Bricalli on behalf of Faculty Of Engineering, Architecture & Info Tech