Combustor for treating waste gas and waste liquid of dinitrogen tetroxide and hydrazine propellants and control method

A technology for dinitrogen tetroxide and waste liquid treatment, which is applied in the direction of combustion methods, combustion types, incinerators, etc., and can solve the problems of waste gas and waste liquid treatment devices that cannot be shared, environmental pollution, and personnel safety hazards, etc., and achieves a compact structure , good structural strength and high reliability

Active Publication Date: 2017-12-26
XIAN AEROSPACE PROPULSION INST
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Dinitrogen tetroxide / hydrazine (such as anhydrous hydrazine, methylhydrazine, unsymmetrical dimethylhydrazine, etc.) propellant is one of the commonly used propellant combinations for liquid rocket engines in my country. Toxic chemicals, among them, the LC of dinitrogen tetroxide 50 (inhalation of rats for 4h) is 126mg / m 3 , LD of hydrazine 50 LD of 60mg / kg, methylhydrazine 50 LD of 32mg / kg, unsymmetrical dimethylhydrazine 50 122mg / kg, if the exhaust gas and waste liquid of dinitrogen tetroxide / hydrazine (such as anhydrous hydrazine, methylhydrazine, unsymmetrical dimethylhydrazine, etc.) propellants produced during scientific research, production and testing are not disposed of in a timely and reasonable manner, It will cause environmental pollution and bring serious hidden dangers to the safety of personnel.
[0004] The above-mentioned treatment method and device for waste gas or waste liquid can only treat dinitrogen tetroxide or hydrazine propellant separately, and the treatment devices for waste gas and waste liquid cannot be shared
In the actual use process, it is necessary to deal with the waste gas of dinitrogen tetroxide and hydrazine propellants, and also the waste liquid of dinitrogen tetroxide and hydrazine propellants. The waste gas of dinitrogen and hydrazine propellant, and the device that can process the waste liquid of dinitrogen tetroxide and hydrazine propellant, in order to save cost, simplify system structure, improve space utilization and safety, the present invention is committed to proposing a A burner and control method for treating exhaust gas and liquid of dinitrogen tetroxide / hydrazine propellants, so as to realize the purpose of treating waste gas and liquid of dinitrogen tetroxide and hydrazine propellants with a set of devices

Method used

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  • Combustor for treating waste gas and waste liquid of dinitrogen tetroxide and hydrazine propellants and control method
  • Combustor for treating waste gas and waste liquid of dinitrogen tetroxide and hydrazine propellants and control method
  • Combustor for treating waste gas and waste liquid of dinitrogen tetroxide and hydrazine propellants and control method

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Effect test

Embodiment 1

[0060] The present invention proposes a device for the treatment of dinitrogen tetroxide / hydrazine propellant waste gas and waste liquid, aiming at the current situation that there is no device capable of processing dinitrogen tetroxide waste gas and waste liquid as well as hydrazine propellant waste gas and waste liquid. The burner includes a head 1 for igniting premixed gas, a body 2 for waste gas and waste liquid treatment, and a tail nozzle 3. The head 1 is located at the front end of the body 2 and the body 2 is coaxially installed, and the tail nozzle 3 is located at the end of the body 2 and installed coaxially with the body 2, see figure 1 and figure 2 , the head 1 provides kerosene / air premixed gas for ignition, and the body 2 mainly burns the waste gas and waste liquid that needs to be treated; the head inner pipe 11 and the head outer pipe 12 are coaxially installed, and the front part of the head inner pipe 11 The position is equipped with a welding straight-thro...

Embodiment 2

[0064] The structure and overall scheme of the burner used for the treatment of dinitrogen tetroxide / hydrazine propellant waste gas and waste liquid are the same as in Embodiment 1, the difference is that the ignition kerosene nozzle 14 is a tangential hole single-component centrifugal nozzle, which can ensure that the kerosene atomization fineness. The ignition kerosene enters from the ignition kerosene channel through the tangential hole of the ignition kerosene nozzle 14, and is sprayed into the atomization zone from the outlet of the nozzle for secondary atomization and mixing under the action of ignition air, and the mixed gas is further mixed and ignited in the mixing zone to form High temperature rich combustion gas. The ignition air channel is a straight hole evenly distributed on the side of the front section of the step-shaped mixing tube. In this example, the cross-section of the hole is circular.

Embodiment 3

[0066] The structure and general scheme of the burner used for the treatment of dinitrogen tetroxide / hydrazine propellant waste gas and waste liquid are the same as those in Embodiments 1 and 2. The head inner tube 11, the head outer tube 12, the secondary air equalizing plate 17, the body Part inner pipe 21, body outer pipe 22, tail nozzle 3, module mounting seat 23 without air channel, module mounting seat 24 with air channel, N 2 o 4 Waste liquid treatment module 26, N 2 o 4 Waste gas treatment module 27, hydrazine waste gas treatment module 28, hydrazine waste liquid treatment module 29, ignition kerosene nozzle 14, stepped mixing tube 15, igniter seat 25 and head cover 13 are all made of stainless steel; 2 o 4 Waste liquid treatment module 26, N 2 o 4 The waste gas treatment module 27, the hydrazine waste gas treatment module 28, and the hydrazine waste liquid treatment module 29 are threadedly connected to the installation seat, which is convenient for disassembly a...

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PUM

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Abstract

The invention provides a combustor for treating waste gas and waste liquid of dinitrogen tetroxide and hydrazine propellants and a control method. The combustor comprises a head for providing ignition premixed gas, a body for treating the waste gas and the waste liquid and a tail spray pipe. Kerosene and air are supplied by multiple paths; an ignition oxidant and ignition fuel are controlled to be in a partial fuel-rich state so as to guarantee reliable ignition; a two-stage sudden expansion structure plays a role in flame stabilizing; through grouped combustion and different nozzle structural modes, the waste gas and the waste liquid can be combusted fully, and it is guaranteed that the emission content of the dinitrogen tetroxide is smaller than 800 ppm and the emission content of the hydrazine propellants is smaller than 0.6 ppm. The combustor has the advantages of good structural strength, reliable ignition, complete gas combustion, nontoxic tail gas and the like and can be used for treating the waste gas and the waste liquid of the dinitrogen tetroxide and the hydrazine propellants.

Description

technical field [0001] The invention belongs to the technical field of harmless treatment of toxic substances, and mainly relates to the treatment of dinitrogen tetroxide / hydrazine propellant waste gas and waste liquid, in particular to a burner for the treatment of dinitrogen tetroxide / hydrazine propellant waste gas and waste liquid The control method can treat the exhaust gas and waste liquid produced by dinitrogen tetroxide / hydrazine propellant. Background technique [0002] Dinitrogen tetroxide / hydrazine (such as anhydrous hydrazine, methylhydrazine, unsymmetrical dimethylhydrazine, etc.) propellant is one of the commonly used propellant combinations for liquid rocket engines in my country. Toxic chemicals, among them, the LC of dinitrogen tetroxide 50 (inhalation of rats for 4h) is 126mg / m 3 , LD of hydrazine 50 LD of 60mg / kg, methylhydrazine 50 LD of 32mg / kg, unsymmetrical dimethylhydrazine 50 122mg / kg, if the exhaust gas and waste liquid of dinitrogen tetroxide / hy...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23G7/04F23G7/06F23G5/44F23G5/50
CPCF23G5/44F23G5/50F23G7/04F23G7/06
Inventor 杨岸龙尚冬琴费俊张锋李龙飞牛晓辙陈帆
Owner XIAN AEROSPACE PROPULSION INST
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