Airflow cooling type multi-electrode high-energy igniter

Abstract

The invention belongs to the technical field of aero-engine combustion chambers, and discloses an airflow cooling type multi-electrode high-energy igniter. The igniter comprises a multi-electrode sparking plug, a cooling hole, a cooling airflow channel, a circulation hole, an outer shell and a mounting seat, the multi-electrode sparking plug coincides with the axis of the outer shell, and the multi-electrode sparking plug is nested in the outer shell; the top end plane of the multi-electrode sparking plug is sunken inwards to form a discharge concave cavity with the outer shell; cooling holes which are uniformly distributed in the circumferential direction are formed in the top end plane, close to the edge, of the outer shell; a circulation hole is formed in the side wall of the outer shell, a circular seam type cooling airflow channel is arranged on the inner wall of the outer shell, the cooling airflow channel is connected with the cooling hole and the circulation hole, and an installation base is arranged at the rear end of the outer shell. The igniter can effectively solve the problems that an aero-engine is poor in ignition reliability and short in service life under the high-altitude extreme condition, the ignition reliability of an engine combustion chamber under the extreme condition is improved, and the service life is prolonged.

Description

technical field [0001] The invention belongs to the technical field of aero-engine combustion chambers, and in particular relates to an airflow-cooled multi-electrode high-energy igniter. Background technique [0002] After the aero-engine is turned off at high altitude, the parameters such as the intake temperature and pressure of the combustion chamber drop rapidly, the viscosity of the fuel increases, and the oxygen content decreases, which adversely affects the atomization, evaporation, ignition, flame propagation and other links. The secondary ignition of the engine combustion chamber faces the extreme conditions of low pressure and low temperature, and requires a more reliable high-performance igniter. [0003] The igniter of the main combustion chamber of an aero-engine generally adopts 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 lo...

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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