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[1]韩长霖,田 原.某缩尺推力室燃烧和传热特性研究[J].火箭推进,2020,46(01):28-34.
　HAN Changlin,TIAN Yuan.Study on combustion and heat transfer characteristics of a scaled trust chamber[J].Journal of Rocket Propulsion,2020,46(01):28-34.
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某缩尺推力室燃烧和传热特性研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 46 期数: 2020年01期 页码: 28-34 栏目: 研究与设计 出版日期: 2020-02-29
Title:
Study on combustion and heat transfer characteristics of a scaled trust chamber
作者:
韩长霖; 田 原
(北京航天动力研究所,北京 100076)
Author(s):
HAN Changlin;  TIAN Yuan
(Beijing Aerospace Propulsion Institute, Beijing 100076, China)
关键词:
火箭发动机;  推力室;  燃烧仿真;  传热仿真;  计算流体力学
Keywords:
rocket engine;  thrust chamber;  combustion simulation;  heat transfer simulation;  CFD
分类号:
V434.13文献标识码:A 文章编号:1672-9374(2020)01-0028-07
摘要:
为了研究冷却剂的流动方向和推进剂的质量流量对推力室燃烧和传热过程带来的影响,以某型氢氧火箭发动机的推力室缩比试验件为研究对象,对推力室的燃烧和传热过程进行了数值仿真。改变冷却剂的流动方向,最高壁面温度相差1.04%,最高壁面热流密度相差0.544%,冷却剂温升相差0.233%,出口压力相差3.803%,分析发现,改变冷却剂的流动方向,对推力室内部的燃烧过程和壁面传热效率影响很小,冷却剂的流动方向会影响壁面温度分布。推进剂质量流量提升22.29%,室压提升22.17%,燃烧效率降低0.55%,最高壁温提升9.16%,最高热流密度提升17.48%,冷却剂温升提高13.05%,分析发现,提升推进剂质量流量会导致推力室壁面温度和冷却剂温升的提高,由于缩比发动机反应空间小燃烧不够充分,提升推进剂质量流量会使燃烧效率有所下降。
Abstract:
To study the influence of mass flow rate of propellant and the flow direction of coolant on combustion and heat transfer process of the trust chamber, the scaled thrust chamber of a certain type of hydrogen-oxygen rocket engine was taken as the research object, and its combustion and heat transfer process was simulated. When the coolant flow direction was changed, the maximum wall temperature varied by 1.04%, the maximum wall heat flux varied by 0.544%, the temperature rise of coolant varied by 0.233% and the coolant outlet pressure varied by 3.803%. The research shows that the direction of coolant flow has little effect on the combustion and heat transfer processes, and it affects the wall temperature distribution. When the mass flow rate of propellant increased by 22.29%, the chamber pressure increased by 22.17%, the combustion efficiency decreased by 0.55%, the maximum wall temperature increased by 9.16%, the maximum heat flux increased by 17.48% and the temperature rise of coolant increased by 13.05%. The improvement of propellant mass flow rate will lead to the increase of the wall temperature and coolant temperature rise. Because the combustion is not sufficient due to the small reaction space in the scaled engine, improving the coolant mass flow rate will reduce the combustion efficiency.

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备注/Memo

收稿日期:2019-03-27; 修回日期:2019-05-10基金项目:民用航天技术预先研究项目(D010401)作者简介:韩长霖(1993—),男,硕士,研究领域为液体火箭发动机设计

更新日期/Last Update: 2020-02-25