Abstract
The use of a laser-ignited expanding flame as a virtual particle for seedless velocimetry of a flammable mixture is described and demonstrated, a method referred to as flame image velocimetry. Within an expanding flame, the burned gas is nominally stagnant relative to the local flow field, such that the motion of the flame centroid can be interpreted as an advected particle and serve as the basis of a single-point velocity measurement. This technique is applied to study the post-reflected-shock (region-5) environment in a shock tube using propane and n-heptane as fuels, lean equivalence ratios (0.3 \(\le \phi \le\) 0.9), and oxidizers consisting of 18.1% to 21.4% O2 balanced with combinations of nitrogen, argon, and helium diluents; thermodynamic conditions spanned the temperature and pressure ranges 571 K \(\le\) T5 \(\le\) 1076 K and 1.0 atm \(\le\) P5 \(\le\) 1.9 atm. A novel imaging configuration is devised to provide simultaneous, dual-perspective, high-speed images of expanding flames ignited 10.3 cm from the end wall of a shock tube. From the resulting images, the three-dimensional velocity field of the region-5 core gas is measured, revealing near-zero velocities in the radial directions and small, but measurable, velocities along the axis of the shock tube. Two conceptual models for axial region-5 velocity are developed: residual velocity resulting from the attenuation of the incident and reflected shock waves and pressure-change-induced velocity associated with temporal variations in the post-reflected-shock pressure. While neither model alone is predictive of the measured axial velocities, their combination systematically recovers the measured results, suggesting that these two conceptual models, based on experimentally measured pressures, are sufficient to predict the region-5 velocity in shock-tube experiments.
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Acknowledgements
This work was supported by the National Science Foundation under award number 1940865, contract monitor Dr. John Daily. Additional support was provided by the U.S. Army Research Laboratory and U.S. Army Research Office under contract/grant number W911NF-17-1-0420. A. J. Susa recognizes the U.S. Department of Defense for financial support through a NDSEG Fellowship. Additional thanks is provided to LaVision for providing the demonstration HS-IRO-X unit used in this work.
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Both authors contributed to the study conception. A.J. Susa designed and performed the experiments, conducted the data analysis, developed the theoretical models, and prepared the first draft of the manuscript; R.K. Hanson provided resources and feedback throughout. Both authors contributed to manuscript revisions and approved the final manuscript.
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A partial, preliminary version of this study was presented at the 12th U.S. National Combustion Meeting, May 24-26, 2021 under the title “Flame-drift velocimetry and flame morphology measurements with dual-perspective imaging in a shock tube.”
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Susa, A.J., Hanson, R.K. Flame image velocimetry: seedless characterization of post-reflected-shock velocities in a shock-tube. Exp Fluids 63, 37 (2022). https://doi.org/10.1007/s00348-022-03388-8
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DOI: https://doi.org/10.1007/s00348-022-03388-8