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Rotational flow torch igniter based on 3D printing forming

A torch igniter, 3D printing technology, applied in the direction of combustion method, combustion chamber, combustion equipment, etc., can solve the problems of difficult to realize miniaturization design, easy ablation of spark plug tip, narrow adaptability to variable working conditions, etc. Effects of thermal protection problems, prolonging gas residence time, shortening body length

Active Publication Date: 2021-01-19
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] In order to overcome the problems existing in the existing torch igniter such as low ignition reliability, easy ablation of the spark plug tip, narrow adaptability to variable working conditions, poor thermal protection performance, serious welding deformation, and difficulty in realizing miniaturized design, the present invention provides a A swirl torch igniter based on 3D printing

Method used

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  • Rotational flow torch igniter based on 3D printing forming
  • Rotational flow torch igniter based on 3D printing forming
  • Rotational flow torch igniter based on 3D printing forming

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Embodiment

[0049] Such as figure 1 , figure 2 As shown, the basic structure of the 3D printing-based swirl torch igniter of the present invention includes an electric spark plug rod 1, a torch ignition tube 2 and a copper sealing gasket 3;

[0050] The spark plug rod 1 and the torch ignition tube 2 are connected through threads, and rely on the copper sealing gasket 3 to realize high-pressure sealing;

[0051] The torch ignition tube 2 includes a head section 4, a body section 5, a throat nozzle section 6 and a tail section 7 integrally formed by 3D printing;

[0052] Such as figure 2 , 3 , 4, the head pipe section 4 includes a central hole 8, an oxidizer interface 9, an oxidant annular gas collection chamber 10, an oxidant nozzle 11, a fuel interface 12, an ignition fuel annular gas collection chamber 13, an ignition fuel nozzle 14 and a body pipe section 5. The chamber pressure measurement interface 15 connected to the front end;

[0053] The central hole 8 is opened axially alo...

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Abstract

The invention discloses a rotational flow torch igniter based on 3D printing forming. The rotational flow torch igniter comprises an electric spark plug rod, a torch ignition tube and a red copper sealing gasket, wherein the torch ignition tube comprises a head tube section, a body tube section, a throat nozzle section and a tail tube section which are integrally arranged in a 3D printing mode; amain working principle of the rotational flow torch igniter is as follows: ignition combustion is carried out in an ignition chamber in the head tube section, secondary combustion is carried out in asecondary combustion chamber of the body tube section, and tertiary blending combustion is carried out in the throat spray tube section, so that the ignition starting process is stable, the combustionprocess is sufficient, and the combustion working reliability of the igniter is greatly improved; and oxidizing agent rotational flow can be arranged on the head tube section to protect the electricspark plug rod, a rotational flow field is arranged in the secondary combustion chamber to form gas film protection on the body tube section, connecting and fastening parts with a thrust chamber are reasonably designed, the appearance structure of the torch igniter is simplified, the miniaturization design of the torch igniter is achieved, the process complexity and cost are reduced, and the manufacturing period is shortened.

Description

technical field [0001] The present invention relates to a torch igniter, in particular to a swirling flow torch igniter based on 3D printing, which can be applied to liquid oxygen methane engine ignition, high-performance attitude and orbit control propulsion power, or other combustion chambers that require miniaturization. Background technique [0002] It is difficult to control the transient start process of the liquid oxygen / methane engine, and the mechanism of the ignition process is complicated, which is one of the technical difficulties in the development of the liquid oxygen / methane engine. In order to quickly adapt to the development needs of liquid oxygen / methane engines, a lot of experimental research work has been done on ignition technology at home and abroad: the United States aims at the power development of the Altair lunar lander and the service module of the Orion spacecraft, mainly focusing on the LOX / LCH4 Two ignition methods, electric spark and glow plug,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28F23R3/38
CPCF23R3/283F23R3/286F23R3/38
Inventor 王勇陈宏玉李舒欣刘占一陈鹏飞杨尚荣周康
Owner XIAN AEROSPACE PROPULSION INST
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