液体火箭发动机自然循环回路预冷非稳态数学模型

陈二锋; 厉彦忠; 程向华; 余锋

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液体火箭发动机自然循环回路预冷非稳态数学模型

专题研究 | 更新时间：2025-07-09

- 液体火箭发动机自然循环回路预冷非稳态数学模型
- Unsteady Mathematic Models of Natural Circulation Loop Precooling of Liquid Rocket Engine
- 西安交通大学学报 2008年42卷第9期页码：1127-1131
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
  
  : 2007-10-29. 作者简介:陈二锋(1980-),男,博士生;厉彦忠(联系人),男,教授,博士生导师. 基金项目:教育部高等学校博士学科点专项科研基金资助项目(20060698021);长江学者和创新团队发展计划资助项目(IRT0746)
- DOI：
  中图分类号： V434.14
- 网络首发：2008-09-10，
  
  纸质出版：2008
- 稿件说明：
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陈二锋, 厉彦忠, 程向华, 等. 液体火箭发动机自然循环回路预冷非稳态数学模型[J]. 西安交通大学学报, 2008,42(9):1127-1131.

Unsteady Mathematic Models of Natural Circulation Loop Precooling of Liquid Rocket Engine[J]. 2008, 42(9): 1127-1131.
陈二锋, 厉彦忠, 程向华, 等. 液体火箭发动机自然循环回路预冷非稳态数学模型[J]. 西安交通大学学报, 2008,42(9):1127-1131. DOI：

Unsteady Mathematic Models of Natural Circulation Loop Precooling of Liquid Rocket Engine[J]. 2008, 42(9): 1127-1131. DOI：

摘要

针对液体火箭发动机自然循环回路预冷过程中的非稳态流动与传热问题

构建了一组涵盖主要传热工况的管壁与低温流体间的传热模型

耦合了循环回路的释热方程和低温流体间的流动传热方程

并采用二分法迭代求解自然循环回路预冷过程中的非稳态循环流量

建立了液体火箭发动机自然循环回路预冷的一维非稳态均相流动数学模型. 与已有传热模型相比

在膜态沸腾阶段引入了反环状流膜态沸腾模型和弥散流膜态沸腾模型

保证了膜态沸腾从全液相到全气相过渡过程中物理意义上的逻辑自洽性

并以输送管为例

验证了液体火箭发动机自然循环回路预冷模型的有效性.

Abstract

The heat transfer models between the pipe wall and the cryogenic liquid were established to investigate the unsteady flow and heat transfer process of a natural circulation loop precooling of a liquid rocket engine. The models couple the heat release equation of the circulation loop and the flow and heat transfer equations of the cryogenic liquid. Moreover

the one-dimensional unsteady homogenous flow mathematic models were set up and solved with the bisection method to obtain the unsteady flow rate of the natural circulation loop. Unlike the existing precooling models

both the inverted annular model and the dispersed model are adopted in the prediction of filming boiling

which ensures the logicality integrity of the transition from full liquid region to full gas region. In addition

the unsteady precooling models of the natural circulation loop of a liquid rocket engine were validated by the calculation of a supply pipe.

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references

钟轶魁, 陈国邦. 低温液体火箭发动机循环预冷模拟试验研究 [D]. 杭州:浙江大学机械与能源工程学院, 2003.

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KAWAJI M, BANERJEE S. Application of a multifield model to reflooding of a hot vertical tube:model structure and interfacial phenomena [J]. ASME Journal of Heat Transfer, 1987, 109(1): 204-211.

HEDAYATPOVR A. Transient two-phase flow of cryogenic fluid in a vertical transfer line during the cooldown process [D]. Knoxiville, Tennessee,USA:Mechanical Engineering, University of Tennessee, 1990.

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张育林, 刘昆, 程谋森. 液体火箭发动机动力学理论与应用 [M]. 北京: 科学出版社, 2005.

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SABNICK H D, KRULLE G. Numerical simulation of transient in feed systems of cryogenicrocket engines [C]∥31st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. San Diego, California,USA: AIAA,1995: 95-2967.

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