Characteristics of cascaded fuel injectors within an accelerating scramjet combustor

Landsberg, Will O., Wheatley, Vincent and Veeraragavan, Ananthanarayanan (2016) Characteristics of cascaded fuel injectors within an accelerating scramjet combustor. AIAA Journal, 54 12: 3692-3700. doi:10.2514/1.J054815

Author Landsberg, Will O.
Wheatley, Vincent
Veeraragavan, Ananthanarayanan
Title Characteristics of cascaded fuel injectors within an accelerating scramjet combustor
Journal name AIAA Journal   Check publisher's open access policy
ISSN 0001-1452
Publication date 2016-06-24
Year available 2016
Sub-type Article (original research)
DOI 10.2514/1.J054815
Open Access Status Not Open Access
Volume 54
Issue 12
Start page 3692
End page 3700
Total pages 9
Place of publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Collection year 2017
Language eng
Formatted abstract
Performances of cascaded hydrogen injectors within an accelerating scramjet combustor were characterized via a three dimensional numerical study. Two streamwise-aligned jets are employed, with the upstream injector half the diameter of the rear jet. Each are inclined at 45 deg to the freestream and achieve a jet-to-freestream momentum ratio of unity. Performance was evaluated over a range of freestream Mach numbers, modeling combustor entrance conditions on an accelerating access-to-space scramjet trajectory. Distance between injectors was varied to estimate the optimum jet-to-jet spacing to achieve robust performance across the Mach number range. It is shown that the downstream injector benefits jointly from shielding effects induced by the smaller upstream injector, as well as its increased diameter. Injector spacings greater than two total jet diameters Dt displayed improved absolute jet penetration, spanwise spread, and entrainment rates over an equivalent single injector across all Mach numbers. Jet bow shock pressure recovery was improved at spacings above 4Dt. Unique optimal injector spacings existed for each performance metric, at each freestream Mach number examined. Although no universal optimum spacing was determined, spacings between 4 and 6Dt provided substantial performance enhancements over single injectors, throughout the accelerating scramjet flight conditions.
Keyword Cascaded hydrogen injectors
Scramjet combustor
Q-Index Code C1
Q-Index Status Provisional Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
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Created: Tue, 19 Jul 2016, 11:06:10 EST by Anand Veeraragavan on behalf of School of Mechanical and Mining Engineering