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Ignition characteristics of a high-energy jet plasma igniter in an aeroengine afterburner
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DOI：10.1016/j.jppr.2026.06.001.png)
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Abstract
En 中文
With the increasing thrust-to-weight ratio demands of modern aeroengines, afterburner ignition performance requirements have become more stringent. To broaden the ignition boundary and enhance ignition capability under extreme conditions, a high-energy jet plasma igniter was developed and its ignition characteristics examined. Analysis focused on the ignition process, ignition delay, and ignition boundary. Results confirmed a two-stage ignition process: the self-ignition process of the igniter and the process of igniting the fuel-air mixture in the afterburner with the jet flame of the igniter. The durations of these stages constitute the total ignition delay. The experimental results show that the igniter has a wide working range and can successfully ignite between 0.63 and 16.91 excess air coefficient, covering the inlet velocity of the combustion chamber from 5.56 to 52.78 m/s. At Tin = 293 K and Win = 1000 m3/h, the ignition delay time in the second stage ranged from a minimum of 100.26 ms to a maximum of 314.99 ms. These results verified the significant advantages of the high-energy jet plasma igniter in effectively expanding the ignition boundary and improving ignition reliability.
Keywords:
High-energy jet igniter
Plasma
Afterburner
Ignition boundary
Ignition delay time
Aeroengine
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