Thermal compression effects within a fundamental, hydrogen-fuelled scramjet

Article


Vanyai, Tristan, Brieschenk, Stefan, Bricalli, Mathew, Sopek, Tamara and McIntyre, Timothy J.. 2021. "Thermal compression effects within a fundamental, hydrogen-fuelled scramjet." Aerospace Science and Technology. 110, pp. 1-16. https://doi.org/10.1016/j.ast.2021.106499
Article Title

Thermal compression effects within a fundamental, hydrogen-fuelled scramjet

ERA Journal ID3574
Article CategoryArticle
AuthorsVanyai, Tristan (Author), Brieschenk, Stefan (Author), Bricalli, Mathew (Author), Sopek, Tamara (Author) and McIntyre, Timothy J. (Author)
Journal TitleAerospace Science and Technology
Journal Citation110, pp. 1-16
Article Number106499
Number of Pages16
Year2021
Place of PublicationFrance
ISSN1270-9638
1626-3219
Digital Object Identifier (DOI)https://doi.org/10.1016/j.ast.2021.106499
Web Address (URL)https://www.sciencedirect.com/science/article/abs/pii/S1270963821000110
Abstract

The impact of thermal compression on combustion has been studied experimentally in a hydrogen-fuelled, non-uniform scramjet flowpath. The experimental model consisted of a three-dimensional inlet, a constant area rectangular combustor, and a single-ramp expansion nozzle, all having a constant width, and was tested at an equivalent Mach 10 flight condition with 58 kPa dynamic pressure. Combustion was suppressed in different regions of the combustor by injecting helium as a replacement for hydrogen fuel in either spanwise half of the engine. Thermal compression effects increased the combustion-induced pressure rise by across the majority of the combustor for an equivalence ratio of 0.8, however a shock-related artefact dominated similar measurements for a case with an equivalence ratio of 1.0. Over a smaller region at the end of the combustor, the combustion-induced pressure rise was increased by and for equivalence ratios of 0.8 and 1.0, respectively. Time-integrated OH emission signals increased by 19% and 31%, whilst time-resolved signals increased by 54% and 35%, for equivalence ratios of 0.8 and 1.0, respectively. This study presents the first experimental evidence of thermal compression directly increasing combustion-induced pressure rise in a scramjet engine.

KeywordsDynamic pressures; Equivalence ratios; Experimental evidence; Experimental modeling; Flight conditions; Hydrogen-fuelled; Scramjet engines; Thermal compressions
ANZSRC Field of Research 2020400106. Hypersonic propulsion and hypersonic aerothermodynamics
510299. Atomic, molecular and optical physics not elsewhere classified
401205. Experimental methods in fluid flow, heat and mass transfer
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Byline AffiliationsUniversity of Queensland
Institution of OriginUniversity of Southern Queensland
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