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On-line Access: 2024-08-20

Received: 2023-07-16

Revision Accepted: 2023-10-24

Crosschecked: 2024-08-20

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Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Xinlin LIU

https://orcid.org/0000-0001-7439-854X

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Journal of Zhejiang University SCIENCE A 2024 Vol.25 No.8 P.631-649

http://doi.org/10.1631/jzus.A2300365


Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine


Author(s):  Xinlin LIU, Jun SUN, Zhuohang JIANG, Qinglian LI, Peng CHENG, Jie SONG

Affiliation(s):  Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   peakdreamer@163.com

Key Words:  Liquid oxygen/liquid methane (LOX/LCH4) rocket engine, Gas film cooling, Regenerative cooling, Heat transfer characteristics


Xinlin LIU, Jun SUN, Zhuohang JIANG, Qinglian LI, Peng CHENG, Jie SONG. Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine[J]. Journal of Zhejiang University Science A, 2024, 25(8): 631-649.

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author="Xinlin LIU, Jun SUN, Zhuohang JIANG, Qinglian LI, Peng CHENG, Jie SONG",
journal="Journal of Zhejiang University Science A",
volume="25",
number="8",
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year="2024",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A2300365"
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%T Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine
%A Xinlin LIU
%A Jun SUN
%A Zhuohang JIANG
%A Qinglian LI
%A Peng CHENG
%A Jie SONG
%J Journal of Zhejiang University SCIENCE A
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%@ 1673-565X
%D 2024
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A2300365

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T1 - Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine
A1 - Xinlin LIU
A1 - Jun SUN
A1 - Zhuohang JIANG
A1 - Qinglian LI
A1 - Peng CHENG
A1 - Jie SONG
J0 - Journal of Zhejiang University Science A
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EP - 649
%@ 1673-565X
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PB - Zhejiang University Press & Springer
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DOI - 10.1631/jzus.A2300365


Abstract: 
The thermal protection of rocket engines is a crucial aspect of rocket engine design. In this paper, the gas film/regenerative composite cooling of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine thrust chamber was investigated. A gas film/regenerative composite cooling model was developed based on the Grisson gas film cooling efficiency formula and the one-dimensional regenerative cooling model. The accuracy of the model was validated through experiments conducted on a 6 kg/s level gas film/regenerative composite cooling thrust chamber. Additionally, key parameters related to heat transfer performance were calculated. The results demonstrate that the model is sufficiently accurate to be used as a preliminary design tool. The temperature rise error of the coolant, when compared with the experimental results, was found to be less than 10%. Although the pressure drop error is relatively large, the calculated results still provide valuable guidance for heat transfer analysis. In addition, the performance of composite cooling is observed to be superior to regenerative cooling. Increasing the gas film flow rate results in higher cooling efficiency and a lower gas-side wall temperature. Furthermore, the position at which the gas film is introduced greatly impacts the cooling performance. The optimal introduction position for the gas film is determined when the film is introduced from a single row of holes. This optimal introduction position results in a more uniform wall temperature distribution and reduces the peak temperature. Lastly, it is observed that a double row of holes, when compared to a single row of holes, enhances the cooling effect in the superposition area of the gas film and further lowers the gas-side wall temperature. These results provide a basis for the design of gas film/regenerative composite cooling systems.

液氧/甲烷火箭发动机气膜/再生复合冷却特性研究

作者:刘新林,孙郡,蒋卓航,李清廉,成鹏,宋杰
机构:国防科技大学,高超声速冲压发动机技术重点实验室,中国长沙,410073
目的:液体火箭发动机热防护设计一直以来都是液体火箭发动机设计的关键。本文旨在针对液氧/甲烷火箭发动机推力室建立气膜/再生复合冷却传热计算模型,并提出一种复合冷却方法。
创新点:1.提出一种气膜冷却和再生冷却相结合的复合冷却方法;2.建立气膜/再生复合冷却传热计算模型;3.开展6kg/s级气膜/再生复合冷却推力室热试车实验,并通过实验验证计算模型的准确性;4.基于复合冷却传热计算模型,开展不同结构参数与工况参数下复合冷却传热特性分析。
方法:1.通过理论推导,建立液体火箭发动机推力室气膜/再生复合冷却传热计算模型;2.通过开展热试车实验,验证传热计算模型的准确性;3.通过数值模型计算,开展不同结构参数与工况参数下复合冷却传热特性分析。
结论:1.气膜/再生复合冷却传热计算模型具有较高的准确性;与实验结果相比,冷却剂温升预测误差小于10%。2.与再生冷却相比,复合冷却性能显著提高;较高的气膜流量可以带来更高的冷却效率和更低的燃气侧壁温。3.膜的引入位置对冷却性能有较大影响;优化后的气膜冷却使壁温分布更加均匀,峰值更低。4.与单层气膜相比,双层气膜可以增强气膜叠加区域的冷却效果,并进一步降低该区域的燃气侧壁温。

关键词:液氧/甲烷发动机;气膜冷却;再生冷却;传热特性

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

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