|Table of Contents|

Study on optimal gas film parameters of near-injection region in thrust chamber(PDF)

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

Issue:
2018年02期
Page:
10-17
Research Field:
研究与设计
Publishing date:

Info

Title:
Study on optimal gas film parameters of near-injection region in thrust chamber
Author(s):
GAO Xingfeng;  ZHANG Jianwei;  SUN Bing;  WANG Taiping
School of Astronautics,Beihang University, Beijing 100191, China
Keywords:
thrust chamber;  numerical simulation;  orthogonal test method;  cooling efficiency;  combustion efficiency
PACS:
V434.2-34
DOI:
-
Abstract:
A three-dimensional numerical simulation of the gas-gas combustion chamber with the multi-element injector with gas film cooling was investigated to obtain the optimal parameters that affect the gas film cooling of the near-injection region in the thrust chamber of the hydrogen-oxygen rocket engine. In the numerical model, the standard k-ε model and the eddy-dissipation concept model are used to simulate the turbulence and combustion process respectively. The orthogonal test method is used to analyze the effect of the different film parameters. The analysis results show that the gas film can reduce the wall temperature of combustor in the near-injection region effectively and homogenize the wall temperature distribution, play a role in thermal protection of the injector head in a certain extent, and flow rate ratio of the gas film has greater influence on the cooling efficiency and the uniformity in the circumferential direction in comparison with the structure of the gas film inlet. The more homogeneous cooling distribution of the gas film can be achieved by selecting the appropriate gas film flow parameter and gas film inlet structure. The injection of the film has a great influence on the combustion efficiency, especially for the structural parameters of the film inlet. The results obtained in this study could be used to provide a reference for the design of gas film cooling.

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