A pre-combustion type aero-engine plasma igniter

Abstract

The invention discloses a pre-combusted aircraft engine plasma igniter. The pre-combusted aircraft engine plasma igniter comprises an outer tube, a ceramic tube fuel channel, a cathode portion, an anode, an insulation sleeve, a bushing and a top cover; the cathode portion is installed on the middle-lower portion of the ceramic tube fuel channel in a sleeving mode, and a nozzle is arranged at the front end of the ceramic tube fuel channel; the insulation sleeve is installed on the middle-upper portion of the cathode portion in a sleeving mode and arranged in the outer tube; air inlet holes areformed in the outer wall of the lower portion of the outer tube, the anode is arranged under the air inlet holes, the upper portion of the anode is located in the outer tube and is in threaded connection with the outer tube, and the anode is a hollow revolving body; the cathode portion comprises a cathode base and a cathode, the upper portion of the cathode is in threaded connection with the lowerportion of the cathode base, and a spiral groove is formed in the middle of the inner wall of the anode; the lower end of the bushing is fixedly connected with the upper end of the cathode base; andthe top cover is installed outside the bushing in a sleeving mode, and the lower portion of the top cover is fixedly connected with the upper end of the outer tube. According to the pre-combusted aircraft engine plasma igniter, the ceramic tube fuel channel is additionally installed in the cathode portion, a reaction occurs outside the anode, therefore, electrodes are protected, the safety is improved, and the insulating problem is well solved.

Description

technical field [0001] The invention belongs to the technical field of aero-engines, in particular to a pre-combustion type aero-engine plasma igniter. Background technique [0002] The combustion chamber is a core component of an aero-engine, where continuous, high-velocity airflow burns. Combustion flames are easily blown out in such high-velocity airflows, so reliable ignition of the combustion chamber is critical during engine start-up. The success rate of ignition is directly related to the safe and reliable operation of the entire power plant, which puts forward higher requirements on the performance of the ignition device. At present, the ignition method used in the ignition device of the main combustion chamber of the aero turbine engine is electric nozzle ignition; the ignition method used in the ignition device of the afterburner mainly includes electric nozzle ignition, pre-chamber ignition, thermal jet ignition and catalytic ignition There are certain limitatio...

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Problems solved by technology

[0007] In the Chinese invention patent with the patent number of 201410568885, an elongated arc plasma jet igniter is disclosed, but there are several serious problems in the invention patent: (1) When the igniter is ignited, the arc is concentrated on the cathode Somewhere at the tip, due to the extremely high arc temperature, it is easy to ablate the cathode; (2) The igniter does not solve the insulation problem of the fuel channel well, and the fuel versatility is poor

[0008] Disclosed a kind of pre-chamber plasma jet igniter in existing research, but it has following several more serious problems: (1) this pre-chamber plasma jet igniter reacts near the anode, adopts anode The side-entry fuel method, this type of igniter greatly increases the temperature near the electrode, which easily damages the electrode and shortens the service life of the igniter, which is not conducive to practical applications and increases the probability of safety problems; (2) The structure of the igniter is relatively complicated, and the fuel inlet is located at the front end, which is not convenient for inserting into various chambers, and is not convenient for the application in the actual process; (3) The front end of the tungsten needle of the igniter is relatively sharp, and the arc is concentrated on a certain place at the tip of the cathode during ignition , because the arc temperature is extremely high, it is easy to ablate the cathode; (4) The igniter does not solve the insulation problem of the fuel channel well, and the fuel versatility is poor

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