An Experimental Investigation of a Thermal Compression Scramjet with OH Imaging

Paper


Vanyai, Tristan, Bricalli, Mathew, Sopek, Tamara, Brieschenk, Stefan and McIntyre, Timothy J.. 2015. "An Experimental Investigation of a Thermal Compression Scramjet with OH Imaging." 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2015). Glasgow, Scotland 06 - 09 Jul 2015 Reston, United States. https://doi.org/10.2514/6.2015-3610
Paper/Presentation Title

An Experimental Investigation of a Thermal Compression Scramjet with OH Imaging

Presentation TypePaper
AuthorsVanyai, Tristan (Author), Bricalli, Mathew (Author), Sopek, Tamara (Author), Brieschenk, Stefan (Author) and McIntyre, Timothy J. (Author)
Journal or Proceedings TitleProceedings of the 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2015)
ERA Conference ID60012
Number of Pages12
Year2015
Place of PublicationReston, United States
Digital Object Identifier (DOI)https://doi.org/10.2514/6.2015-3610
Web Address (URL) of Paperhttps://arc.aiaa.org/doi/10.2514/6.2015-3610
Conference/Event20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2015)
AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Event Details
20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2015)
Event Date
06 to end of 09 Jul 2015
Event Location
Glasgow, Scotland
Event Details
AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Abstract

Scramjet engines must be designed to operate over a range of Mach numbers. In order to maintain robust starting characteristics at low freestream Mach numbers, the inlet contraction ratio must be minimized, reducing performance at high Mach numbers. The technique of thermal compression can be used to maintain robust combustion at low mean pressure and temperature, improving the performance of low inlet contraction ratio engines over a range of Mach numbers. This paper examines a scramjet engine with a three-dimensional inlet that induces spanwise gradients of pressure and temperature, producing high inlet compression on one side and low inlet compression on the other. The effect of combustion in each half on pressure throughout the entire flowfield is examined by suppressing combustion on either half of the combustor through injecting either a combusting fuel, hydrogen, or a non-combusting replacement, helium. Two optical techniques are used to examine how the concentration of the OH radical varies throughout the combustor. Images of OH* Chemiluminescence and OH Planar Laser-Induced Fluorescence (PLIF) map the concentration and production of OH radicals indicating chemical activity throughout the combustion process. The thermal compression effect is isolated, and is shown to increase combustion-induced pressure rise in a scramjet engine.

KeywordsChemical activities; Combustion pro-cess; Experimental investigations; Freestream mach number; Oh planar laser induced fluorescences; Pressure and temperature; Starting characteristic; 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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