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A kind of scramjet combustor flow direction linear plasma igniter and ignition method

A technology of plasma and scram stamping, which is applied in the direction of plasma, machine/engine, gas turbine device, etc., can solve the problems of lack of reliable repeated ignition methods, meet the needs of repeated ignition, improve ignition capacity, and have strong ignition capacity Effect

Active Publication Date: 2021-12-10
AIR FORCE UNIV PLA
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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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  • A kind of scramjet combustor flow direction linear plasma igniter and ignition method
  • A kind of scramjet combustor flow direction linear plasma igniter and ignition method
  • A kind of scramjet combustor flow direction linear plasma igniter 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

Provided is a scramming combustion chamber flowing to a linear plasma igniter, which is composed of an insulator (101), a discharge cathode (102), a discharge connection electrode (103), and a discharge anode (104). The discharge cathode (102) is connected to the cathode of the plasma power supply (301) by a wire built into the insulator (101); the discharge anode (104) is connected to the anode of the plasma power supply (301) by a wire built into the insulator (101); The electrode (103), the coupling capacitor (302), and the anode of the plasma power supply (301) are sequentially connected in series. Compared with the existing igniter and powder-type ignition method, the scramjet combustion chamber flow-to-linear plasma igniter and ignition method of the present invention are easy to be used in combination with the existing aero-engine drive power supply, thereby meeting the requirement of multiple repeated ignitions; Compared with the spark plug ignition method, the ignition method proposed by the present invention has a larger initial fire core and stronger spark energy, so the ignition capability is stronger.

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 Patents(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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