Optimizing combustion performance in a solid rocket scramjet engine

Jie Liu*, Ning fei Wang, Jian Wang, Zi yan Li

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

43 Citations (Scopus)

Abstract

To enhance combustion efficiency of a boron-based propellant solid rocket scramjet (SRS) engine, this study attempted a new organization scheme combining cavity and pneumatic slope. To optimize the proposed system, a series of numerical simulations were performed, and through orthogonal design and single factor analysis, the key factors were determined. The developed two-phase flow simulation has been verified by the full-scale ground test, given an error within 10%. The results show that for both combustion efficiency and total pressure recovery, the influence of gas injection mode is much greater than the ratio of the length to depth of the concave cavity as well as the cavity depth. And the combustion performance has proved to be optimized via the enlarged low speed area near the cavity and the strengthened particles reflux.

Original languageEnglish
Article number105560
JournalAerospace Science and Technology
Volume99
DOIs
Publication statusPublished - Apr 2020

Keywords

  • Combustion efficiency
  • Orthogonal design
  • Solid propellant
  • Solid rocket scramjet
  • Two-phase flow

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Liu, J., Wang, N. F., Wang, J., & Li, Z. Y. (2020). Optimizing combustion performance in a solid rocket scramjet engine. Aerospace Science and Technology, 99, Article 105560. https://doi.org/10.1016/j.ast.2019.105560