|Table of Contents|

Experimental study on porous plate transpiration cooling of thrust chamber(PDF)

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

Issue:
2011年05期
Page:
9-12
Research Field:
研究与设计
Publishing date:

Info

Title:
Experimental study on porous plate transpiration cooling of thrust chamber
Author(s):
GAO Xiang-yu;  SUN Ji-guo
Beijing Aerospace Propulsion Institute, Beijing 100076, China
Keywords:
transpiration cooling; porous plate; liquid rocket engine; thrust
PACS:
V434-34
DOI:
-
Abstract:
Hot fire tests were performed on subscale thrust chamber to investigate the transpiration cooling characteristics of thrust chamber injector porous face plate cooled by H2 of room tempe- rature. Five times tests were conducted under the conditions: combustion chamber pressure of 3.9-7.6 MPa, and O/F mixture ratio of 2.8-7.2. The investigation demonstrates that the hot gas wall temperature of the porous plate is 680-830 K under the test conditions. The engineering flow resistance function applied to thrust chamber porous face plate was obtained.

References:

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