|Table of Contents|

Numerical analysis of H2 transpiration cooling for thrust chamber porous plate(PDF)

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

Issue:
2012年05期
Page:
13-17
Research Field:
研究与设计
Publishing date:

Info

Title:
Numerical analysis of H2 transpiration cooling for thrust chamber porous plate
Author(s):
GAO Xiang-yu;  SUN Ji-guo;  TIAN Yuan
Beijing Aerospace Propulsion Institute, Beijing 100076, China
Keywords:
transpiration coolingnumerical calculationporous plateH/O rocket enginethrust chamber
PACS:
V434+.14
DOI:
-
Abstract:
In order to investigate the transpiration cooling characteristics of H/O rocket engine thrust chamber injector porous plate, the one-dimensional local thermal non-equilibrium numerical model was adopted to conduct the heat transfer computation and analysis. The hydrogen coolant thermo-physical properties varied with both temperature and pressure, and heat transfer between the porous media and coolant were considered for the computation model. The influence of porous media thermal conductivity, porosity, sphere diameter and heat flow density on porous plate transpiration cooling were analyzed. The investigation demonstrates that optimization of porous plate material with high thermal conductivity can reduce the gas side plate temperature and temperature gradient of porous plate. The porosity should be 0.1~0.2. The heat transfer capacity between the porous media and coolant is obviously reduced with the increase of sphere diameter, but the temperature of the gas side plate decreases at first and then increases.

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