Premixed propellant injector with integrated ignition and tempering prevention functions

A propellant and anti-backfire technology, which is applied in the direction of jet propulsion devices, machines/engines, rocket engine devices, etc., can solve problems such as the inability to use anti-backfire measures, and achieve the effects of preventing backfire, uniform injection and ignition

Active Publication Date: 2020-05-08
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Nitrous oxide-based premixed propellants have an extremely fast flame propagation rate, which precludes the use of these currently available flashback protection measures

Method used

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  • Premixed propellant injector with integrated ignition and tempering prevention functions
  • Premixed propellant injector with integrated ignition and tempering prevention functions

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Embodiment Construction

[0021] The technical solutions of the present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0022] The present invention provides a premixed propellant injector with integrated ignition and anti-backfire functions. Its working principle is as follows: the premixed propellant enters the liquid collection chamber 5 along the propellant inlet conduit 11, and passes through the injection body of porous material. 6 and the direct-current injection hole 7 are uniformly sprayed and atomized, and a low-velocity recirculation zone is formed at the ignition end surface of the electric spark plug 1, and the ignition and stable combustion of the propellant are realized by the electric spark plug 1, and the micron-scale flow channel of the porous material injection body 6 It can effectively prevent the combustion flame from backfiring.

[0023] like figure 1 As shown, the premixed propellant injector with integrated i...

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Abstract

The invention relates to a premixed propellant injector with integrated ignition and tempering prevention functions, and solves the tempering problem of combustion of nitrous oxide-based premixed propellant. The premixed propellant injector comprises an electric spark plug, an electric spark plug seat, a liquid collecting cavity outer shell, a porous material injection body, an injection plate anda propellant inlet conduit, wherein the electric spark plug base and the injection plate are sequentially sleeved at the bottom end of the electric spark plug, the porous material injection body is nested in an annular groove at the top end of the injection plate, a plurality of direct current injection holes are formed in the bottom end of the injection plate, one ends of the direct current injection holes communicate with the porous material injection body, and the other ends of the direct current injection holes communicate with a combustion chamber; the liquid collecting cavity outer shell is sleeved outside the electric spark plug base and forms an annular liquid collecting cavity with the porous material injection body and the injection plate; and the propellant inlet conduit is arranged outside the liquid collecting cavity outer shell. The propellant enters the liquid collecting cavity along the propellant inlet conduit, and is uniformly sprayed and atomized through the porousmaterial injection body and the direct current injection holes, and ignition is realized by the electric spark plug.

Description

technical field [0001] The invention relates to a propellant injector, in particular to a premixed propellant injector with integrated ignition and anti-backfire functions. Background technique [0002] Nitrous oxide-based premixed propellant is a new type of oxygen-burning premixed propellant compounded with nitrous oxide and hydrocarbon fuels such as ethylene, acetylene or ethane. This type of propellant is non-toxic, non-polluting, high specific impulse performance, The advantages of simple engine system, self-pressurization of the storage tank, deep throttling, and wide storage temperature range are considered to be one of the most promising new propellants to replace hydrazine-based toxic propellants in the future. However, since this type of propellant is a premixed propellant, flashback is very easy to occur during ignition and combustion. Once flashback occurs, the entire propellant supply system including the storage tank will explode, causing serious safety acciden...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/52F02K9/95
CPCF02K9/52F02K9/95
Inventor 张锋冯建畅胡洪波王勇杨伟东杨岸龙
Owner XIAN AEROSPACE PROPULSION INST
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