Experiments on Plasma-Assisted Combustion in a Supersonic Flow: Optimization of Plasma Position in Relation to the Fuel Injector

• Published in: Aerospace Lab no. 10
• Main Authors: Savelkin, K.V., Yarantsev, D.A., Leonov, S.B.
• Format: Journal Article
• Language: English
• Published: Alain Appriou 01.12.2015
• Subjects: Engineering Sciences; Reactive fluid environment; DISCHARGE; COMBUSTION; PLASMA
• ISSN: 2107-6596
• DOI: 10.12762/2015.AL10-08

The results of an experimental study of plasma-induced ethylene ignition and flameholding in a supersonic model combustor are presented in the paper. The experimental combustor has a cross-section of 72 mm (width) x 60 mm (height) and length of 600 mm. The fuel is directly injected into the supersonic airflow through wall orifices. The flow parameters are: Mach number M=2, static pressure Pst=160-250 Torr, stagnation temperature T0=300 K and total air flow rate Gair≤0.9 kg/s. The near-surface quasi-DC electrical discharge is generated by a series of flush-mounted electrodes, providing an electrical power deposition of Wpl=3-24 kW. The scope of the experiments includes the characterization of the discharge interacting with the main flow and fuel injection jet, a parametric study of ignition and flame front dynamics and a comparison of three plasma generation schemes: the first two examine upstream and downstream locations of plasma generators in relation to the fuel injectors. The third pattern follows a novel approach of a combined mixing/ignition technique, where the electrical discharge is distributed along the fuel jet, starting within the fuel injector. The last pattern demonstrates a significant advantage in terms of the flameholding limit. The experiments are supported by gas temperature and H2O vapor concentration measurements by Tunable Diode-Laser Absorption Spectroscopy (TDLAS). The technique studied in this work has weighty potential for high-speed combustion applications, including cold start/restart of scramjet engines and support of the transition regime in a dual-mode scramjet and during off-design operation.