Micro gas and gas double-component propellant combustor

A two-component, propellant technology, used in jet propulsion devices, machines/engines, rocket engine devices, etc., can solve the problems of fast flow rate in the combustion chamber of the engine, no explanations and reports, and no data collected. Conducive to ignition, improve ignition reliability, and reduce the effect of ignition core heat loss

Active Publication Date: 2017-09-19
SHANGHAI INST OF SPACE PROPULSION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the high-altitude and low-pressure environment, the combustion chamber of a conventional engine has a fast flow rate and a low concentration of combustibles, making it difficult to ignite an

Method used

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  • Micro gas and gas double-component propellant combustor
  • Micro gas and gas double-component propellant combustor
  • Micro gas and gas double-component propellant combustor

Examples

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Embodiment Construction

[0025] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0026] Such as Figure 1 to Figure 5 As shown, the burner of the miniature gas and gas bipropellant of the present invention includes a body 1, a nozzle 2, a nozzle 3, a fuel inlet 4, an oxidant inlet 5, an electric nozzle 6 and a sealing ring 7; the nozzle 2 is installed in the body 1, The nozzle 3 is welded on the body 1, the lower end surface of the nozzle 3 is closely attached to the upper end surface of the nozzle 2, the fuel inlet 4 is welded on the nozzle 3, the oxidant inlet 5 is welded on...

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Abstract

The invention provides a micro gas and gas double-component propellant combustor. The combustor comprises a body and the like; a spraying opening is formed in the body, a nozzle is welded to the body, the lower end face of the nozzle and the upper end face of the spraying opening are tightly attached, a fuel inlet is welded to the nozzle, an oxidizing agent inlet is welded to the body, a sparking plug is connected with the body through a thread, the sparking plug and the body are sealed through a seal ring, an annular gas collection cavity is formed by the body and the nozzle, a pre-mixing cavity is formed by the spraying opening and the nozzle, the body is provided with a combustion chamber and a spraying pipe, the spraying opening is provided with a shrinkage type flowing channel, the nozzle is provided with a fuel injection hole and an oxidizing agent injection hole, gaseous fuel enters the pre-mixing cavity through the fuel inlet and the fuel injection hole, and the reliable ignition and stable combustion functions are achieved.

Description

technical field [0001] The invention relates to a combustor, in particular to a combustor for a micro gas and gas bicomponent propellant. Background technique [0002] Miniature gas / gas bicomponent engines generally use oxygen / hydrocarbon fuel as propellant, and use electric igniter to ignite. It has the advantages of green, non-toxic, high energy, clean combustion, and simple system. It is often used as an ignition torch for large engines. And it has application potential on other power devices. In the high-altitude and low-pressure environment, the combustion chamber of conventional engines has a fast flow rate and a low concentration of combustibles, making it difficult to ignite and stabilize the flame. [0003] Still do not find explanation and report with similar technology of the present invention at home, also do not collect similar data at home and abroad yet. Contents of the invention [0004] Aiming at the defects in the prior art, the object of the present in...

Claims

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Application Information

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IPC IPC(8): F02K9/62F02K9/52
CPCF02K9/52F02K9/62
Inventor 吉林许宏博贾晴晴曾夜明杨芳芳关亮金盛宇
Owner SHANGHAI INST OF SPACE PROPULSION
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