|Table of Contents|

Numerical study of heat transfer in variable cross-section cooling channels of LOX/methane rocket engines(PDF)

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

Issue:
2019年02期
Page:
9-15
Research Field:
研究与设计
Publishing date:

Info

Title:
Numerical study of heat transfer in variable cross-section cooling channels of LOX/methane rocket engines
Author(s):
ZHANG Ming;  SUN Bing
(School of Astronautics, Beihang University, Beijing 100191, China)
Keywords:
methane;  transcritical;  coupled heat transfer;  rocket engine;  regenerative cooling;  sudden contraction/sudden expansion
PACS:
V434.14
DOI:
-
Abstract:
In order to improve the cooling efficiency of regenerative cooling channels of liquid rocket engine thrust chamber, the numerical simulation of the coupled heat transfer in the variable cross-section cooling channels of the LOX/methane engine thrust chamber was carried out to investigate the effects of the aspect ratio on the turbulent flow and convective heat transfer of the transcritical methane in this paper.An improved iterative coupling method was used for the three-dimensional coupling calculation of the hot gas, the cooling channel and the coolant domain.The research results show that when the cooling channel cross-sectional area is constant, increasing the aspect ratio of the cooling channel can reduce the maximum hot-gas-side wall temperature at the throat.The larger the cooling channel aspect ratio is, the greater the coolant pressure loss is.However, excessive aspect ratio will lead to a sharp increase in pressure loss, and the effect of further reducing the maximum temperature of the hot-gas-side wall at the throat is not obvious.The hot-gas-side wall temperature drops at the sudden contraction/sudden expansion structures of variable cross-section cooling channel.And the magnitude of the decrease increases as the aspect ratio decreases.In the large aspect ratio cooling channel, the area where the heat transfer deterioration occurs near the lateral wall surface at the throat is limited, mainly in the lower half of the rib side wall.This paper provides a reference for the design of variable cross-section regenerative cooling channels of the thrust chamber.

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Last Update: 2019-04-30