Provided is an aero-engine air
rotational flow plasma igniter. An insulating sleeve and a supporting sleeve are installed inside a shell, the insulating sleeve is arranged on one side of a separating plate inside the shell, the supporting sleeve is arranged inside the shell, and an
air chamber is formed between the outer surface of the supporting sleeve and the inner surface of the shell. An
anode sleeve is sleeved at one end, provided with the supporting sleeve, of the shell. A swirler is arranged inside the
anode sleeve, and the end surface of the swirler makes contact with the end surface of the supporting sleeve. A
cathode installation base is arranged inside the insulating sleeve, and the end surface of the
cathode installation base makes contact with a
cathode binding post in a
coaxial cable. The external thread end of a cathode is fixed inside the cathode installation base and sequentially penetrates through the supporting sleeve and the swirler from top to bottom, and the arc end of the cathode extends out of the lower end surface of the swirler. The aero-engine air
rotational flow plasma igniter does not change the structure and the position of an
electric spark igniter originally installed in an engine
combustor, penetrates through the outer duct of an engine, is installed on the outer wall of the
combustor vertically, improves reliability of products, and has the advantages of being small in size, light in weight, simple in structure, and convenient to use and maintain.