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Numerical simulation and experimental verification of RBCC combustor in ramjet mode(PDF)

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

Issue:
2022年06期
Page:
69-73,91
Research Field:
目次
Publishing date:

Info

Title:
Numerical simulation and experimental verification of RBCC combustor in ramjet mode
Author(s):
HUANG Leping;  DOU Feilong;  LIU Hao;  LI Guangxi
(Xian Aerospace Propulsion Institute, Xian 710100, China)
Keywords:
RBCC combustor ramjet mode kerosene
PACS:
V235
DOI:
-
Abstract:
In order to explore the combustion characteristics of a rocket based combined cycle(RBCC)engine with kerosene in ramjet mode,a numerical simulation method was proposed to predict and analyze the flow and combustion process in the combustion chamber. The 3D internal flow field of a RBCC combustor with strut injectors and a cavity flame holder in ramjet mode were simulated numerically. The calculated wall pressure curve is in good agreement with the results obtained by ground tests and a flight test,indicating that the calculation model is reasonable and practicable. By analyzing the combustor pressure,Mach number,gas composition and other parameters,it can be found that the current combustion chamber structure can realize the stable and efficient combustion of liquid kerosene fuel in ramjet mode. Compared with the cold flow,the pressure rise can reach more than 5 times. The struts can effectively improve the mixing performance of kerosene fuel and air. There is a reflux zone at the downstream of the step for mounting rocket,which is conducive to combustion and flame stability. By adjusting the fuel supply law of injectors such as the cavity and the struts,the utilization rate of inlet oxygen can be improved and more sufficient combustion can be achieved.

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