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Safe processing device of low-temperature hydrogen in rocket engine thrust chamber

A technology for rocket engine and safe handling, which is applied in rocket engine units, jet propulsion units, machines/engines, etc. to ensure safety and improve safety.

Inactive Publication Date: 2013-06-05
BEIJING INST OF AEROSPACE TESTING TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the treatment of low-temperature hydrogen in the thrust chamber is a new topic in the development and

Method used

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  • Safe processing device of low-temperature hydrogen in rocket engine thrust chamber
  • Safe processing device of low-temperature hydrogen in rocket engine thrust chamber
  • Safe processing device of low-temperature hydrogen in rocket engine thrust chamber

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Embodiment Construction

[0021] Such as figure 1 As shown, the present invention is mainly composed of a hydrogen cylinder 1, a manual switch 2, a pressure reducing valve 3, a solenoid valve 4, a hydrogen pipeline 5, a nitrogen drainage ring 7, a high-energy electronic igniter 8, a high-voltage cable 9, a conductive rod 10, and a high-energy semiconductor Electric nozzle 11 and hydrogen nozzle 12 are composed of hydrogen bottle 1, manual switch 2, pressure reducing valve 3, solenoid valve 4, hydrogen pipeline 5, and hydrogen nozzle 12 to form an ever-burning torch; high-energy electronic igniter 8, high-voltage cable 9, The conductive rod 10 and the high-energy semiconductor electric nozzle 11 form an electronic ignition system; the nitrogen gas diversion ring 6 serves as a low-temperature hydrogen flame diversion system. When the present invention works, first turn on the manual switch 2, adjust the opening of the decompression valve 3 so as to adjust the gas source pressure of the hydrogen cylinder ...

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Abstract

The invention discloses a safe processing device of low-temperature hydrogen in a rocket engine thrust chamber. An everburning torch is arranged at the outlet of a thrust chamber nozzle, is powered by hydrogen, and has a wide flame combustion mixing ratio range. When the engine is ignited to start, a large amount of hydrogen can be exhausted from the thrust chamber to be ignited by the everburning torch; and then the ignited hydrogen is drained by a large amount of nitrogen to zones far away from the engine. A nitrogen draining ring is arranged on the periphery of the thrust chamber, at least three rows of pinholes are radially arranged on the periphery of the nitrogen draining ring and play a draining role. Nozzles are welded on the axial periphery of the nitrogen draining ring horizontally spray high-speed nitrogen in a direction perpendicular to the axis of the thrust chamber to achieve the functions of fire-stopping, cooling and fire-extinguishing, thereby improving the safety of engine tests. By connecting a high-voltage cable and a conducting rod in a threaded mode and utilizing ceramic and metallic protecting nets as external heat-proof protection, the safety of the engine tests is improved.

Description

technical field [0001] The invention relates to a hydrogen safety processing device, in particular to a low-temperature hydrogen safety processing device for a rocket engine thrust chamber, which is mainly used for ground tests of a high-thrust hydrogen-oxygen rocket engine, and can safely handle a large amount of low-temperature hydrogen discharged before the thrust chamber is ignited, and belongs to Liquid rocket engine test technology. Background technique [0002] my country's new-generation launch vehicle core first-stage engine uses liquid hydrogen and liquid oxygen as propellants, with a stand-alone thrust of 50 tons. In order to ensure smooth ignition and start of the engine, large-thrust hydrogen-oxygen engines at home and abroad adopt the method of cooling the thrust chamber first and then igniting and starting. Before the engine is ignited, about 100L of liquid hydrogen needs to be discharged, and the volume of hydrogen after gasification can reach 80m 3 , A lar...

Claims

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Application Information

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IPC IPC(8): F02K9/44F02K9/60
Inventor 陈春富张奎好杨思锋孙德刘瑞敏崔海郭素芳白文浩方维朱继鑫王树光
Owner BEIJING INST OF AEROSPACE TESTING TECH
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