|Table of Contents|

Effect of wall thickness on throat wall temperature of space small thrust engines(PDF)

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

Issue:
2011年06期
Page:
34-37
Research Field:
研究与设计
Publishing date:

Info

Title:
Effect of wall thickness on throat wall temperature of space small thrust engines
Author(s):
ZHANG Feng;  ZHONG Wei-cong;  ZHANG Wei-jing
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
wall thickness;  small thrust engine;  throat wall temperature
PACS:
V430-34
DOI:
-
Abstract:
The frequently-used cooling modes for spaceborne small thrust engines and ways usually-used to reduce the throat wall temperature of the thrust chamber are introduced. The possibility of reducing the throat wall temperature by increasing the wall thickness is discussed. The throat wall temperature under the condition of different wall thickness is calculated by simplifying the model. The results show that the throat wall temperature could be reduced by increasing the wall thickness properly.

References:

[1]STECHMAN R C. Film cooling design criteria for small rocket engines, AIAA 68-617 [R]. USA: AIAA, 1968.
[2]GRISSON W M. Liquid film cooling in rocket engines, AD-A234 288 [R]. USA: AD, 1991.
[3]张锋, 仲伟聪. 膜冷却推力室传热计算研究[J]. 火箭推进,2009, 35(4): 34-37.
[4]刘国球. 液体火箭发动机原理[M]. 北京: 中国宇航出版社. 1993.
[5]杨世铭, 陶文铨. 传热学[M]. 北京: 高等教育出版社. 1998.

Memo

Memo:
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Last Update: 1900-01-01