|Table of Contents|

Method to enhance combustion stability margin of high thrust rocket engine(PDF)

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

Issue:
2014年05期
Page:
8-13
Research Field:
研究与设计
Publishing date:

Info

Title:
Method to enhance combustion stability margin of high thrust rocket engine
Author(s):
LI Long-fei;  CHEN Jian-hua;  LIU Zhan-guo
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
liquid rocket engine;  high-frequency combustion instability;  combustion stability margin
PACS:
V434-34
DOI:
-
Abstract:
To overcome the high-frequency combustion instability of spontaneous excitation of high thrust liquid rocket engines (LRE), the main factors (including acoustic frequency of combustor, structural parameters of combustor and geometric structure of coaxial injector) which affect the combustion stability margin of high thrust LOX-kerosene rocket engine are summarized and analyzed. The results show that the propellant combustion area and combustor convergence section close to the injector have great effects on the acoustic inherent frequency of the combustion chamber, the relatively perfect combustion stability can be got when the combustion chamber length is 0.205 times longer than the combustion chamber diameter or is odd number of 0.205, and the maximum oscillation energy can be obtained when the length of the gas-liquid coaxial injector is 0.5 times the first-order tangential oscillation frequency. A combustor design method to enhance combustion stability margin and avoid high-frequency combustion instability is proposed to provide a reference for the engineering design of LRE.

References:

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Last Update: 1900-01-01