Effect of scramjet inlet vortices on fuel plume elongation and mixing rate

Article


Llobet, J.R., Gollan, R.J. and Jahn, I.H.. 2019. "Effect of scramjet inlet vortices on fuel plume elongation and mixing rate ." Aeronautical Journal. 123 (1265), pp. 1032-1052. https://doi.org/10.1017/aer.2019.45
Article Title

Effect of scramjet inlet vortices on fuel plume elongation and mixing rate

Article CategoryArticle
AuthorsLlobet, J.R., Gollan, R.J. and Jahn, I.H.
Journal TitleAeronautical Journal
Journal Citation123 (1265), pp. 1032-1052
Number of Pages21
YearJul 2019
PublisherCambridge University Press
Place of PublicationUnited Kingdom
ISSN0001-9240
2059-6464
Digital Object Identifier (DOI)https://doi.org/10.1017/aer.2019.45
Web Address (URL)https://www.cambridge.org/core/journals/aeronautical-journal/article/effect-of-scramjet-inlet-vortices-on-fuel-plume-elongation-and-mixing-rate/8894C0A97E37718B18CD5C23DB05654C
Abstract

Hypersonic air-breathing propulsion can improve cost and flexibility of Low Earth Orbit (LEO) satellite launch missions. However, at the high flight Mach numbers required for access-to-space, performance margins are extremely tight. Techniques to improve mixing efficiency can push this technology forward. However, these are required to produce a minimal increase in losses and heat loads to be viable. The use of inlet-generated vortices in scramjets for mixing enhancement was previously studied. These vortices interact with the injected fuel plume, stretching it and increasing its effective surface for mixing. Moreover, these vortices are intrinsic to the flowfield. Therefore, contrary to other methods, when using inlet vortices mixing is enhanced without producing additional heat loads or losses. This work studies the vortex-injection interaction through numerical RANS simulations. A non-dimensional variable defining the quality of the plume shape for mixing purposes is proposed. This parameter is used to assess the effect of vortex intensity and injector location on fuel plume shape. The results show the ability of inlet vortices to modify fuel plume shape significantly increasing fuel mixing rate with minimal impact on losses.

KeywordsHypersonic air-breathing propulsion
ANZSRC Field of Research 2020400106. Hypersonic propulsion and hypersonic aerothermodynamics
401204. Computational methods in fluid flow, heat and mass transfer (incl. computational fluid dynamics)
401205. Experimental methods in fluid flow, heat and mass transfer
Byline AffiliationsUniversity of Queensland
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