|Table of Contents|

Heat transfer investigation for 5 kN regeneratively-cooled engine thrust chamber(PDF)

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

Issue:
2012年02期
Page:
32-37
Research Field:
研究与设计
Publishing date:

Info

Title:
Heat transfer investigation for 5 kN regeneratively-cooled engine thrust chamber
Author(s):
SUN Xin;  YANG Cheng-hu
Shanghai Institute of Space Propulsion, Shanghai 201112, China
Keywords:
regenerative coolingheat transferfiring test
PACS:
V434.14-34
DOI:
-
Abstract:
5 kN gimbaled engine adopts the regenerative cooling technology in the thrust chamber design. In order to validate the rationality of the cooling scheme of the thrust chamber, the heat transfer calculation on the regenerative cooling thrust chamber was conducted, and the effects of excess oxidizer coefficient and combustion chamber length on regenerative cooling were analyzed, and an improvement approach for the engine design was put forward. The redesigned engine worked properly in the firing test. It indicates that the improvement approach is effective.

References:

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Memo

Memo:
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Last Update: 1900-01-01