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Simulation and analysis for influence of fuel distribution on scramjet performance(PDF)

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

Issue:
2013年04期
Page:
30-35
Research Field:
研究与设计
Publishing date:

Info

Title:
Simulation and analysis for influence of fuel distribution on scramjet performance
Author(s):
YAO Zhao-hui;  LI Guang-xi;  ZHANG Meng-zheng;  YAN Jun-feng
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
scramjet;  fuel distribution;  engine performance;  combustion mode;  thermal choking
PACS:
V434+.13-34
DOI:
-
Abstract:
Aiming at the influence of the fuel distribution on the flow mechanism in scramjet duct, combustion mode, engine performance and adjustment characteristic, a one-dimensional scramjet analysis model was established. Simulation of flow process in one-stage/two-stage fuel distribution percent is carried under three different cases, including Ma 6/ψ 1, Ma 6/ψ 0.6, Ma 4/ψ 1. Scramjet performance in different fuel distribution is obtained. The analysis results show that the flow mechanism, combustion mode and engine performance are strongly dependent on the one-stage/two-stage fuel distribution percent. For the case of Ma 6/ψ 1, combustion in the duct can be organized in supersonic flow when one-stage combustor fuel distribution is at the range of 30%~70%, whose maximum specific impulse exceeds 800 s. For the case of Ma 6/ψ 0.6, combustion is always organized in supersonic flow even if all the fuel is injected in one-stage combustor, because the total fuel amounts are too small to choke the combustor duct, whose maximum specific impulse exceeds 800 s. For the case of Ma 4/ψ 1, combustion can be organized in subsonic flow and its maximum specific impulse is 1 031.9 s. Furthermore, the one-stage fuel distribution should not be too high, so as to avoid a subsonic combustion disturbance diffusing outside the combustor entrance.

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