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[1]吴有亮,丁煜朔,刘 潇,等.再生冷却推力室准二维传热数值计算[J].火箭推进,2023,49(02):66-73.
　WU Youliang,DING Yushuo,LIU Xiao,et al.Quasi-2D heat transfer calculation method of regenerative cooling thrust chamber[J].Journal of Rocket Propulsion,2023,49(02):66-73.
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再生冷却推力室准二维传热数值计算

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 49 期数: 2023年02期 页码: 66-73 栏目: 目次 出版日期: 2023-04-25
Title:
Quasi-2D heat transfer calculation method of regenerative cooling thrust chamber
文章编号:
1672-9374(2023)02-0066-08
作者:
吴有亮; 丁煜朔; 刘 潇; 刘阳旻; 田 原
(北京航天动力研究所,北京 100076)
Author(s):
WU Youliang;  DING Yushuo;  LIU Xiao;  LIU Yangmin;  TIAN Yuan
(Beijing Aerospace Propulsion Institute, Beijing 100076, China)
关键词:
再生冷却;  传热;  准二维;  温度分层;  边界层
Keywords:
regenerative cooling;  heat transfer;  quasi-2D;  temperature stratification;  boundary layer
分类号:
V434.14
文献标志码:
A
摘要:
为了提高液体火箭发动机传热计算精度,建立了再生冷却推力室准二维传热计算的通用方法。冷却通道内考虑了冷却剂层间导热导致的温度分层效应,燃气侧对流换热既可采用传统Bartz公式,又可直接求解边界层控制方程得到热流密度,最终基于MATLAB开发完成了通用的再生冷却推力室准二维传热程序。利用该程序对某氢氧发动机进行了传热计算,并与一维传热程序和三维CFD传热计算结果进行了对比,结果表明:准二维传热计算方法可以计算出冷却通道内温度分层情况,冷却剂温升、流阻计算值与热试数据吻合较好,误差在10以内,优于一维传热结果,验证了计算方法的有效性; 直接求解边界层控制方程得到的热流密度与三维计算结果吻合较好; 准二维传热计算时间短,效率高。
Abstract:
In order to improve the calculation accuracy of heat transfer, a general quasi-2D model was developed to study heat transfer of thrust chamber.This model takes account of the temperature stratification effect caused by heat conduction between coolant layers.The convective heat transfer on the gas side can be calculated by using Bartz equation or solving the governing equations of boundary layers.Then a quasi-2D heat transfer code was developed based on MATLAB language.Finally, validation of the model was carried out by comparison with the analysis of a rocket thrust chamber obtained by the code of one-dimensional model and CFD solver.The results show that the quasi-2D model can calculate the temperature stratification in the cooling channels.The calculated values of coolant temperature rise and pressure loss are in good agreement with the thermal test data, and the error is less than 10, which is better than the one-dimensional heat transfer results, which verifies the effectiveness of the calculation method.In addition, the heat flux obtained by directly solving the boundary layer governing equation is in good agreement with the CFD results.Finally, the calculation time of quasi-2D model is shortrt and the efficiency is higher.

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备注/Memo

收稿日期:2021-12-25; 修回日期:2022-02-26
基金项目:民用航天科研工程项目(D010103)
作者简介:吴有亮(1993—),男,硕士,工程师,研究领域为液体火箭发动机热防护设计。

更新日期/Last Update: 1900-01-01