Discharge and jet characteristics of gliding arc plasma igniter driven by pressure difference

Stable combustion in an afterburner can help increase the thrust of the engine in a short time, thereby improving the maneuverability of a fighter. To improve the ignition performance of an afterburner, a twin-duct ignition platform was designed to study the performance of a gliding arc plasma igniter in close-to-real afterburner conditions. The research was carried out by a combination of experiments and simulations. The working environment of the igniter was explored through a numerical simulation. The results showed that the airflow ejected from the radiating holes formed a swirling sheath, which increased the anti-interference ability of the airflow jet. The influence of the pressure difference between the inlet and outlet of the igniter (∆p), the flow rate outside the igniter outlet (W₂), and the installation angle (α) on the single-cycle discharge energy (E) as well as the maximum arc length (L) were studied through experiments. Three stages were identified: the airflow breakdown stage, the arc evolution stage, and the arc fracture stage. E and L increased by 107.3% and 366.2%, respectively, with ∆p increasing from 10 to 70 Torr. The relationship between L and ∆p obtained by data fitting is L=3 - 2.47/(1 + (∆p/25)⁴). The relationship of L at different α is L_α=0° > (L_α=45° and L_α=135°) > L_α=180° > L_α=90°. E and L decrease by 18.2% and 37.3%, respectively, when ∆p=45 Torr and W₂ is increased from 0 to 250 l min^-1.