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Flow linear type plasma igniter for scramjet combustor and ignition method

A plasma and scramjet technology, which is applied in plasma, gas turbine devices, machines/engines, etc., and can solve problems such as lack of reliable repeated ignition methods

Active Publication Date: 2020-10-20
AIR FORCE UNIV PLA
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In view of this, in view of the outstanding problem of lack of reliable re-ignition methods in the existing ramjet combustion chamber, the present invention proposes a scramjet combustion chamber flowing to a linear plasma igniter, which consists of an insulator 101, a discharge cathode 102, and a discharge connection electrode 103, a discharge anode 104, a plasma power supply 301, and a coupling capacitor 302; wherein

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  • Flow linear type plasma igniter for scramjet combustor and ignition method
  • Flow linear type plasma igniter for scramjet combustor and ignition method
  • Flow linear type plasma igniter for scramjet combustor and ignition method

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specific Embodiment

[0048] In a specific embodiment of the present invention, the insulator 101 is sintered from high temperature resistant alumina ceramics, the depth of the cavity is 15mm, the length of the bottom of the cavity is 100mm, and the inclination angle of the inclined wall behind the cavity is 45°. The discharge cathode 102, the discharge anode 104, and the discharge connection electrode 103 are processed from high-temperature-resistant metal materials, preferably nickel-based high-temperature alloys. The discharge cathode 102 is composed of a rectangular single metal strip, with an electrode length of 60mm and a width of 10mm. The discharge anode 104 is composed of a rectangular single metal strip with a length of 60 mm and a width of 10 mm. It is installed in the central area of ​​the back of the bottom of the concave cavity at a distance of 10 mm from the rear end and is connected to the anode of the plasma power supply 301 . The discharge connection electrode 103 is composed of 5...

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Abstract

The invention provides a flow linear type plasma igniter for a scramjet combustor. The flow linear type plasma igniter comprises an insulator (101), a discharge cathode (102), a discharge continuationelectrode(103) and a discharge anode (104), wherein the discharge cathode (102) is connected with a cathode of a plasma power supply (301) through a wire arranged in the insulator (101); the discharge anode (104) is connected with an anode of the plasma power supply (301) through a wire arranged in the insulator (101); and the discharge continuation electrode (103), a coupling capacitor (302) andthe anode of the plasma power supply (301) are sequentially connected in series. Compared with a conventional igniter and a gunpowder type ignition method, the low linear type plasma igniter for a scramjet combustor and an ignition method disclosed by the invention are easy to cooperate with a driving power supply of a conventional aeronautic engine for use, so as to meet multiplicating ignitionrequirements. Compared with a plug ignition method, the ignition method provided by the invention has the advantages that the initial fire nuclei is bigger, the spark energy is higher, and the ignition capacity is higher.

Description

technical field [0001] The invention belongs to the design field of a scramjet combustion chamber, and in particular relates to a scramjet combustion chamber flow-to-line plasma igniter and an ignition method, which are suitable for reliable ignition of a scramjet combustion chamber. Background technique [0002] The important military significance and commercial value of the scramjet engine are self-evident, and all major military powers have vigorously studied them. Compared with the turbine engine, the airflow velocity in the combustion chamber of the supercombustion engine exceeds 1000m / s, and the fuel residence time is only on the order of milliseconds, which makes it very difficult for the reliable and stable ignition of the combustion chamber. Although the high-power propellant igniter has strong ignition performance, it cannot meet the multiple ignition needs such as open-ground round-trip, repeated take-off and landing. However, the spark plug igniter often used in...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/266H05H1/34
CPCF02C7/266H05H1/34
Inventor 张志波吴云贾敏崔巍金迪宋慧敏朱益飞梁华李应红李军
Owner AIR FORCE UNIV PLA
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