Open AccessNon-Reacting Examination on Transverse Injection Upstream of Aft Wall Angled Cavities in an Axisymmetric Supersonic Flow
Author(s) -
Shan M. Assis,
S. Jeyakumar,
K. Jayaraman
Publication year - 2019
Publication title -
international journal of recent technology and engineering
Language(s) - English
Resource type - Journals
ISSN - 2277-3878
DOI - 10.35940/ijrte.d1064.1284s219
Subject(s) - scramjet , combustor , mach number , mechanics , injector , stagnation pressure , supersonic speed , stagnation temperature , materials science , rotational symmetry , transverse plane , mixing (physics) , flow (mathematics) , static pressure , nozzle , choked flow , cavity wall , aerospace engineering , stagnation point , physics , engineering , chemistry , structural engineering , thermodynamics , combustion , composite material , heat transfer , organic chemistry , quantum mechanics
Experiments on an air-fueled non-reacting scramjet test facility with four distinct aft wall angled cavity designs were performed in a Mach 1.8 flow field to explore the effects of transverse fuel injection system on scramjet combustors. Axisymmetric combustor cavity models were featured with two consecutive angles being inclined towards the downstream flow direction at the rear end. The wall mounted injector was located upstream from the cavity at a distance of 10 mm. Mixing performance within the various rear wall angled cavities were evaluated and compared with No-injection case for different injection pressures. Results revealed that the flow within the combustor was more uniform mixing compared to No-cavity configuration and was greatly influenced by injection pressures. Increase in injection pressures were characterized by enhanced mixing, greater stagnation pressure loss values and unstable flow.