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Combustion Modes and Unsteady Characteristics during the Condition Transition of a Scramjet Combustor

Author

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  • Dongpeng Jia

    (Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)

  • Yu Pan

    (Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)

  • Ning Wang

    (Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)

  • Chaoyang Liu

    (Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)

  • Kai Yang

    (Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)

Abstract

To investigate the combustion modes and unsteady characteristics during the condition transition of a scramjet combustor, a series of experiments were carried out under the condition of Mach 2.52 supersonic incoming flow, the corresponding stagnation pressure and temperature of which were 1.6 MPa and 1486 K, respectively. A fuel supply system that could dynamically adjust the injection pressure was adopted to simulate the condition transition stage of a scramjet. Based on the advanced combustion diagnosis technique, the transient chemiluminescence image and the wall pressure were recorded during the whole combustion process. Three typical modes of turbulent combustion occurred when the injection pressure drop gradually increased. The jet flame was stable after the condition transition when the injection pressure drop was relatively low. An unstable combustion phenomenon accompanied by intermittent local extinction and reignition could be found near the blowout limits. With a further increase in the injection pressure drop, the flame was blown out quickly during the transition process. In addition, the flame development characteristics during condition transition under stable combustion mode and the effect of injection pressure drop were studied in detail. During the process of switching between the two conditions, the area and light intensity of the flame decreased over time, and the wall pressure was accordingly reduced. As the increase in injection pressure dropped, the intensity of chemical reactions deceased obviously and the transition time became longer.

Suggested Citation

  • Dongpeng Jia & Yu Pan & Ning Wang & Chaoyang Liu & Kai Yang, 2021. "Combustion Modes and Unsteady Characteristics during the Condition Transition of a Scramjet Combustor," Energies, MDPI, vol. 14(9), pages 1-14, April.
    • Handle: RePEc:gam:jeners:v:14:y:2021:i:9:p:2522-:d:545027
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    References listed on IDEAS

    as
    1. Seung-Min Jeong & Jeong-Yeol Choi, 2020. "Combined Diagnostic Analysis of Dynamic Combustion Characteristics in a Scramjet Engine," Energies, MDPI, vol. 13(15), pages 1-21, August.
    2. Stephen M. Neill & Apostolos Pesyridis, 2017. "Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight," Energies, MDPI, vol. 10(11), pages 1-22, November.
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