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Numerical simulation of combustion characteristics for thrust chamber in hydrogen peroxide/kerosene engine(PDF)

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

Issue:
2011年04期
Page:
35-39
Research Field:
研究与设计
Publishing date:

Info

Title:
Numerical simulation of combustion characteristics for thrust chamber in hydrogen peroxide/kerosene engine
Author(s):
LI Qiang;  NIE Song;  LIU Ye-kui;  PAN Liang;  MA Meng-ying
Beijing Aerospace Propulsion Institute, Beijing 100076, China
Keywords:
-
PACS:
V434-34
DOI:
-
Abstract:
The gas-liquid combustion and flow field in HTP/kerosene engine thrust chamber were numerically simulated in the paper. Discrete phase modeling (DPM) and SST k-ω turbulence model were used to simulate the kerosene gas-liquid flow and turbulence respectively. A one-step general reaction model of fuel was employed to simulate the kerosene vapour combustion. The combustion flow field and performance parameters of the combustion chamber were numerically investigated. A foundation for the further numerical research was established in this paper.

References:

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