|Table of Contents|

Numerical study on flow and heat transfer of air precooler in SABRE(PDF)

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

Issue:
2019年05期
Page:
8-16
Research Field:
研究与设计
Publishing date:

Info

Title:
Numerical study on flow and heat transfer of air precooler in SABRE
Author(s):
WEI Xin;  JIN Feng;  LIU Tianyi;  JI Honghu
(College of Energy and Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
Keywords:
precooler;  supercritical helium;  average heat transfer coefficient;  total pressure loss coefficient
PACS:
V438.1
DOI:
-
Abstract:
In order to study the flow and heat transfer characteristics of air precooler in Synergistic Air-Breathing Rocket Engine(SABRE)and provide the technical basis for designing precooler, the effects of tube pitch, tube row, air incidence angle and helium/air heat capacity ratio on the flow and heat transfer of air precooler were numerically studied.The results show that increasing the number of tube rows and reducing the tube spacing can increase the heat transfer power of the precooler and reduce the air outlet temperature.However, they also reduce the average heat transfer coefficient on the air side and helium side, weaken the convective heat transfer coefficient and increase the total pressure loss coefficient of air side.The air incidence angle has little effect on the heat transfer of both sides, but has a significant effect on the total pressure recovery coefficient of air side.Increasing the helium/air heat capacity ratio can reduce the total pressure loss coefficient on the air side, increase the average heat transfer coefficient on both sides, reduce the air outlet temperature and enhance the pre-cooling effect.

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Last Update: 2019-10-25