Single-Shot Temperature Measurements in a Scramjet Combustor Using Thermally Assisted Laser-Induced Fluorescence

Article


Sopek, Tamara, Brieschenk, Stefan, Vanyai, Tristan, Morgan, Richard G. and McIntyre, Timothy J.. 2020. "Single-Shot Temperature Measurements in a Scramjet Combustor Using Thermally Assisted Laser-Induced Fluorescence." AIAA Journal: devoted to aerospace research and development. 58 (8), pp. 3486-3498. https://doi.org/10.2514/1.J058985
Article Title

Single-Shot Temperature Measurements in a Scramjet Combustor Using Thermally Assisted Laser-Induced Fluorescence

ERA Journal ID3575
Article CategoryArticle
AuthorsSopek, Tamara (Author), Brieschenk, Stefan (Author), Vanyai, Tristan (Author), Morgan, Richard G. (Author) and McIntyre, Timothy J. (Author)
Journal TitleAIAA Journal: devoted to aerospace research and development
Journal Citation58 (8), pp. 3486-3498
Number of Pages13
Year2020
PublisherAmerican Institute of Aeronautics and Astronautics
Place of PublicationUnited States
ISSN0001-1452
1533-385X
Digital Object Identifier (DOI)https://doi.org/10.2514/1.J058985
Web Address (URL)https://arc.aiaa.org/doi/10.2514/1.J058985
Abstract

The knowledge of the temperature in the flowfield of the scramjet is critical to the understanding of its performance. This study represents the application of an optical diagnostic technique, thermally assisted laser-induced fluorescence, to the temperature measurements in the combustor of a supersonic combustion engine. The experiments were conducted in the T4 shock tunnel using a scramjet model. Experimental data were obtained by focusing a laser beam into the combustor and exciting the OH radical. A detailed numerical model that simulates all radiative and collisional processes of relevance with the appropriate system of differential equations was developed for the analysis of the influence of energy transfer processes on the fluorescence signal. The population distributions achieved with numerical modeling of the LIF process validated the approach proposed to deduce temperatures. By evaluating the scramjet LIF spectra with a full spectral fit, a temperature distribution across the combustor width was obtained. The experimental results were compared with the computational fluid dynamics simulations of the combustion process.

KeywordsCollisional process; Computational fluid dynamics simulations; Energy transfer process; Fluorescence signals; Laser induced fluorescence; Optical diagnostic techniques; Supersonic combustion; System of differential equations
ANZSRC Field of Research 2020400106. Hypersonic propulsion and hypersonic aerothermodynamics
510299. Atomic, molecular and optical physics not elsewhere classified
510203. Nonlinear optics and spectroscopy
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Byline AffiliationsUniversity of Queensland
Institution of OriginUniversity of Southern Queensland
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