An air-cooled multi-electrode high-energy igniter

Abstract

The invention belongs to the technical field of aero-engine combustion chambers, and discloses an airflow-cooled multi-electrode high-energy igniter. The igniter includes a multi-electrode nozzle, a cooling hole, a cooling air flow channel, a flow hole, an outer casing and a mounting seat; the axis of the multi-electrode nozzle coincides with the outer casing, and the multi-electrode nozzle is nested in the outer casing; The top plane of the electrode nozzle is recessed inward, forming a discharge cavity with the outer casing; the top plane of the outer casing is provided with cooling holes evenly distributed along the circumferential direction near the edge; the side wall of the outer casing is provided with circulation holes, The inner wall of the outer casing is provided with a ring-slit cooling air channel, the cooling air channel is connected with the cooling hole and the flow hole, and the rear end of the outer casing is provided with a mounting seat. The igniter can effectively solve the problems of poor ignition reliability and short service life of the aero-engine under extreme conditions at high altitude, improve the ignition reliability of the engine combustion chamber under extreme conditions, and prolong the service life.

Description

technical field [0001] The invention belongs to the technical field of aero-engine combustion chambers, and in particular relates to an air-cooled multi-electrode high-energy igniter. Background technique [0002] After the aero-engine is extinguished at high altitude, the parameters such as the intake air temperature and pressure of the combustion chamber drop rapidly, the fuel viscosity increases, and the oxygen content decreases, which has adverse effects on atomization, evaporation, ignition, flame propagation and other links. The secondary ignition of the engine combustion chamber faces extreme conditions of low pressure and low temperature, which requires more reliable high-performance igniters. [0003] The main combustion chamber igniter of aero-engine generally uses a semiconductor nozzle based on spark discharge. The discharge of the semiconductor nozzle is concentrated in an arc channel between the central high-voltage electrode and the outer low-voltage electrode...

AI Technical Summary

Problems solved by technology

Under the conditions of high altitude, low pressure and low temperature, fuel atomization, evaporation, and mixing quality are poor. Even if the semiconductor nozzle produces a fire core, it is limited by the volume and penetration of the fire core, and it is difficult to enter the central recirculation area with a high fuel-gas ratio, resulting in ignition fail

[0004] At present, an oxygen supply device is usually added to the engine to solve the problem of high-altitude ignition of the aero-engine, which makes the structure of the ignition system complex and the weight of the engine increases

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