Flow field manipulation via fuel injectors in scramjets

Landsberg, Will O., Gibbons, Nicholas N., Wheatley, Vincent, Smart, Michael K. and Veeraragavan, Ananthanarayanan (2017). Flow field manipulation via fuel injectors in scramjets. In: 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017. 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017, Xiamen, China, (). 6 - 9 March 2017.

Author Landsberg, Will O.
Gibbons, Nicholas N.
Wheatley, Vincent
Smart, Michael K.
Veeraragavan, Ananthanarayanan
Title of paper Flow field manipulation via fuel injectors in scramjets
Conference name 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
Conference location Xiamen, China
Conference dates 6 - 9 March 2017
Convener AIAA
Proceedings title 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
Place of Publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Publication Year 2017
Sub-type Fully published paper
Open Access Status Not yet assessed
ISBN 9781624104633
Total pages 20
Language eng
Formatted Abstract/Summary
In airframe integrated scramjets, non-uniform compression fields combine with thick boundary layers developed over the vehicle forebody, to deliver density stratified flow to the combustor. In high Mach number scramjets fuelled with wall-based injectors, delivering fuel to engine centreline oxygen is a challenge. Here, we exploit the interaction between the density stratified flow, and the vortices generated by a strategically positioned fuel jet to manipulate the flow field, redistributing captured oxygen to more accessible locations. A numerical study was performed, examining the Mach 12 Rectangular-to-Elliptical ShapeTransitioning flow path. With the inlet compressing air into a high density, cowl-side core-flow, hydrogen injection here through a ‘manipulator jet’ imparts vorticity through the bulk of the engine mass flow. The high penetration 30 deg injector allowed hydrogen to pierce the core-flow, aided by the engine’s natural shock train. The injector-induced vortices ensured the centrally located and previously inaccessible air was redistributed to the more accessible cowl-side combustor surface. With the jet bow shock passing through the engine core-flow, engine compression was augmented, yielding an 11% increase in freestream pressure. Total pressure losses are comparable to previous fuelling configurations, with only 0.6% greater losses.
Q-Index Code EX
Q-Index Status Provisional Code
Institutional Status UQ

Document type: Conference Paper
Collections: School of Mechanical & Mining Engineering Publications
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