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Combustion treatment method and test of high pressure oxidizer-rich gas of conventional propellant LRE(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2023年01期
Page:
84-92
Research Field:
目次
Publishing date:

Info

Title:
Combustion treatment method and test of high pressure oxidizer-rich gas of conventional propellant LRE
Author(s):
XIAO Hong;  FANG Xirong;  LI Yue;  LI Longfei;  SUN Haiyu;  WANG Huanran
(Xian Aerospace Propulsion Institute, Xian 710100, China)
Keywords:
N2O4/UDMH propellant oxidizer-rich gas pressure drop water-mixed fuel secondary combustion non-toxic treatment
PACS:
V434.3
DOI:
-
Abstract:
In order to detoxify the oxidizer-rich exhaust gas produced by the N2O4/UDMH gas generator of high-thrust staged combustion cycle rocket engine, a real-time combustion treatment device for high-pressure semi-system test of a liquid engine was developed.Technologies of rapid depressurization and secondary combustion with water-mixed fuel were adopted.The device consists of stabilization chamber and secondary combustion chamber.A significant pressure drop was obtained when the exhaust gas flows through supersonic nozzle and multi-orifice plate in stabilization chamber.The exhaust flow becomes uniform before it flows into the secondary combustion chamber downstream.The water-mixed fuel is sprayed at different positions in the secondary combustion chamber.By controlling mixing ratio and combustion temperature, NOx in the exhaust gas is converted into N2 and CO2.Test results present that the secondary combustion is stable and the structure is reliable.The pressure drop ratio is higher than 95 and the secondary combustion efficiency is over 0.9.The non-toxic treatment is realized, and the treatment flow rate of exhaust gas exceeds 100 kg/s.

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