Effect of injection dynamics on detonation wave propagation in a linear detonation combustor |
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| Affiliation: | 1. School of Aeronautics & Astronautics, Purdue University, West Lafayette, IN 47907, USA;2. School of Mechanical Engineering, Purdue University, West Lafayette, IN 47907, USA;3. Spectral Energies LLC, Beavercreek, OH 45430, USA;4. NASA Glenn Research Center, Cleveland, OH 44135, USA;1. Department of Aerospace Engineering, Texas A&M University, College Station, TX 77840, USA;2. Department of Aerospace Engineering, University of Maryland, College Park, MD 20742, USA;1. Department of Mechanical Engineering, University of Connecticut, Storrs, CT 06269, United States;2. Department of Mechanical Engineering, Stanford University, Stanford, CA 94305, United States;3. Department of Chemical Engineering, Queen’s University, Kingston, Ontario K7L 3N6, Canada;4. Department of Mechanical and Aerospace Engineering, University of California, Irvine, CA 92697, United States;1. Department of Aerospace Engineering, Nagoya University, Furo-cho, Chikusa-ku, Nagoya, Aichi, 464-8603, Japan;2. Institute of Materials and Systems for Sustainability, Nagoya University, Furo-cho, Chikusa-ku, Nagoya, Aichi, 464-8603, Japan;1. Spectral Energies, LLC, 4065 Executive Dr., Beavercreek, OH 45430, USA;2. Air Force Research Laboratory, Wight-Patterson Air Force Base, OH 45433, USA |
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| Abstract: | The effect of reactant injection and mixing on detonation wave propagation is studied in a self-excited, optically-accessible linear detonation combustor operated with natural gas and oxygen. Fuel injection and mixing processes are captured with 100 kHz planar laser induced fluorescence (PLIF) measurements of acetone tracer injected into the fuel stream. Measurements are acquired at multiple orthogonal planes downstream of the reactant injection site to investigate the three-dimensional mixing field in the chamber. The fuel distribution field is correlated with simultaneously acquired OH chemiluminescence measurements that provide a qualitative indication of heat release in the combustor. These measurements are used to provide quantitative information of the fuel injector recovery process and its impact on detonation wave structure across a range of equivalence ratios. While significant differences in the detonation wavefront are observed with change in equivalence ratio, the characterization of the fuel refill process into the chamber after the passage of the detonation wave highlights some key generalizable features. The time available for fuel recovery is consistently between 12 – 19% of the detonation wave period across an equivalence ratio range of 0.83 – 1.48. A linear correlation between injector recovery times and the ratio of the average detonation wave pressure amplitude relative to the pressure drop across the fuel injector is observed. Instantaneous and phase-averaged measurements of acetone-PLIF with the time-coincident OH chemiluminescence images provide qualitative information of wave structure and injection dynamics along with quantification of fuel injector recovery, a key metric that drives combustor operation and performance. These measurements significantly enhance the ability to obtain detailed information on the intra- and inter-cycle spatiotemporal evolution of the reactant refill process and its coupled effects on the detonation wave structure and propagation. |
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