Investigation of transient ignition process in a cavity based scramjet combustor using combined ethylene injectors

Research output: Contribution to journalArticle

Abstract

Large Eddy Simulation (LES) and experiment were employed to investigate the transient ignition and flame propagation process in a rearwall-expansion cavity scramjet combustor using combined fuel injection schemes. The compressible supersonic solver and three ethylene combustion mechanisms were first validated against experimental data and results show in reasonably good agreement. Fuel injection scheme combining transverse and direct injectors in the cavity provides a benefit mixture distribution and could achieve a successful ignition. Four stages are illustrated in detail from both experiment and LES. After forced ignition in the cavity, initial flame kernel propagates upstream towards the cavity front edge and ignites the mixture, which acts as a continuous pilot flame, and then propagates downstream along the cavity shear layer rapidly to the combustor exit. Cavity shear layer flame stabilization mode can be concluded from the heat release rate and local high temperature distribution during the combustion process.

Details

Authors
  • Xiao Liu
  • Zun Cai
  • Yiheng Tong
  • Hongtao Zheng
Organisations
External organisations
  • Harbin Engineering University
  • National University of Defense Technology
Research areas and keywords

Subject classification (UKÄ) – MANDATORY

  • Fluid Mechanics and Acoustics
Original languageEnglish
Pages (from-to)1-7
Number of pages7
JournalActa Astronautica
Volume137
Publication statusPublished - 2017 Aug 1
Publication categoryResearch
Peer-reviewedYes