Numerical study of plasma-assisted ignition and stabilisation of a supersonic hydrogen–air combustion in LAERTE facility by a quasi-DC gliding arc
Year: 2025
Type: article
Abstract: This article presents three-dimensional numerical simulations of the plasma-assisted ignition and stabilisation of a supersonic hydrogen/air combustion in a model scramjet combustor (LAPCAT-II combustion chamber). The simulated conditions correspond to an altitude of 33 km and a flight Mach number of 5, i.e. an inlet temperature and pressure T i = 1400 K and P i = 4 bar. The gliding arc discharge is produced by a Plasma Injector Module (PIM). A macro-model is used to simulate the restrikes of the arc. The simulations couple the gliding arc of 5 A, a hydrogen injection flow with a mass flow rate of 1.5 g·s−1, and the main air crossflow. The gliding arc preferentially restrikes on the right and left sides of the PIM, near the injector. The arc rapidly produces small combustion kernels. Despite the inhomogeneous distribution of the heat release, the arc is able to maintain the combustion.
Authors: A Rocamora, J Labaune, C O Laux, F Tholin
Institutions: Université Paris-Saclay, Office National d'Études et de Recherches Aérospatiales, Département Multi-physique pour l'énergétique, Centre National de la Recherche Scientifique, CentraleSupélec, Laboratoire d'Énergétique Moléculaire et Macroscopique, Combustion, Département Physique, Instrumentation, Environnement et Espace
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: bronze
OpenAlex ID: W4413820913