月基核电源堆芯设计及物理热工特性分析

宁可为; 宋帅; 赵富龙; 谢林; 谭思超

doi:10.13832/j.jnpe.2022.S2.0118

月基核电源堆芯设计及物理热工特性分析

doi: 10.13832/j.jnpe.2022.S2.0118

宁可为^{1, 2,},
宋帅^{1, 2, 3},
赵富龙^{1, 2, ,},
谢林^{1, 2},
谭思超^{1, 2}

1.
哈尔滨工程大学核科学与技术学院，哈尔滨，150001
2.
哈尔滨工程大学黑龙江省核动力系统与装置重点实验室，哈尔滨，150001
3.
北京师范大学核科学与技术学院，北京，100875

基金项目: 黑龙江省自然科学基金 (YQ2020A002)，黑龙江省博士后基金 (LBH-Z19013)

详细信息

作者简介:
宁可为（1997—），男，博士研究生，核科学与技术专业， E-mail: ningkewei@hrbeu.edu.cn

通讯作者:
赵富龙，E-mail: zfl970041611@foxmail.com

中图分类号: TL325
计量
- 文章访问数: 149
- HTML全文浏览量: 58
- PDF下载量: 28
- 被引次数: 0
出版历程
- 收稿日期: 2022-07-20
- 修回日期: 2022-09-19
- 刊出日期: 2022-12-31

Core Design and Analysis of Physical and Thermal Characteristics of Lunar-based Nuclear Power Source

Ning Kewei^{1, 2
,},
Song Shuai^{1, 2, 3},
Zhao Fulong^{1, 2
, ,},
Xie lin^{1, 2},
Tan Sichao^{1, 2}

1.
Harbin Engineering University, College of Nuclear Science and Technology, Harbin 150001, China
2.
Heilongjiang Provincial Key Laboratory of Nuclear Power System & Equipment, Harbin Engineering University, Harbin 150001, China
3.
Beijing Normal University, College of Nuclear Science and Technology, Beijing, 100875, China

摘要

摘要: 核能具有长续航、长寿期的特点，能够为月球探索提供可靠能源保障。本文提出月基300 kW（热功率）热离子反应堆方案，通过蒙特卡罗方法进行堆芯物理特性分析，并通过堆芯单通道流动换热计算对反应堆热工安全进行数值模拟研究。计算结果表明，方案能够实现10 a寿期，具备足够停堆深度，但部分温度区间内出现正温度反馈，需要依赖精细控制满足反应堆安全性要求；处于月面微重力环境下，冷却剂流速不小于0.9 m/s时，堆芯最热通道不超过热工安全限值。
- 月基核电源 /
- 热离子反应堆 /
- 物理特性 /
- 换热特性
Abstract: Nuclear energy has the characteristics of long endurance and long life, which can provide reliable energy guarantee for lunar exploration. In this paper, the lunar-based 300kWt thermionic reactor scheme is proposed. The core physical characteristics are analyzed by Monte Carlo method, and the reactor thermal safety is studied by numerical simulation through the single channel flow and heat exchange calculation of the core. The calculation results show that the scheme can achieve 10 years’ lifetime and has sufficient shutdown depth, but there is positive temperature feedback in some temperature intervals, and it needs to rely on the fine control to meet the reactor safety requirements. In the lunar microgravity environment, when the coolant flow rate is not less than 0.9m/s, the hottest channel of the core does not exceed the thermal safety limit.
- Lunar-based nuclear power source /
- Thermionic reactor /
- Physical characteristics /
- Heat exchange characteristics

HTML全文

图 1 燃料元件及堆芯概念设计图

Figure 1. Conceptual Design of Fuel Elements and Reactor Core　　　　　　　

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图 2 反射层温度对k_eff的影响

Figure 2. Influence of Reflector Temperature on k_eff

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图 3 k_eff和燃耗深度随时间变化

Figure 3. k_eff and Burnup Depth Change Versus Time　　　　　　　　

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图 4 寿期内主要核素质量随时间变化

Figure 4. Mass of Major Nuclides During Lifetime Change Versus Time

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图 5 冷却剂通道及网格划分图

Figure 5. Coolant Channel and Meshing

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图 6 通道出口温度分布云图

Figure 6. Temperature Distribution Nephogram at Channel Outlet　　　　　　

下载: 全尺寸图片幻灯片

表 1 堆芯计算结果

Table 1. Reactor Core Calculation Results

参数名	参数值
有效增殖因子	1.01940
总中子注量率/（cm⁻²·s⁻¹）	3.41×10¹⁶
裂变率/（cm⁻³·s⁻¹）	2.06×10¹⁴
中子泄漏率/（cm⁻²·s⁻¹）	1.196×10¹⁴
平均每次裂变释放的中子数/个	2.50
平均每次裂变释放的能量/ MeV	202.30

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表 2 不同能量中子注量率及裂变反应份额

Table 2. Neutron Flux and Fission Reaction Share of Different Energies

能量	中子注量率/ （cm⁻²·s⁻¹）	中子注量率占比/%	裂变反应率/ (cm⁻³·s⁻¹）	引起裂变反应占比/%
0~0.625 eV	1.57×10¹⁵	4.6	7.65×10¹²	3.7
0.625 eV~0.1 MeV	1.40×10¹⁶	41.1	7.53×10¹³	36.6
0.1~2 MeV	1.85×10¹⁶	54.3	1.23×10¹⁴	59.7
全部	3.41×10¹⁶	100	2.06×10¹⁴	100

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表 3 堆芯在不同温度下的温度系数

Table 3. Temperature Coefficient of Core at Different Temperatures

温度/K	300~600	600~900	900~1200	1200~1500	1500~1800
温度系数/(10⁻⁵ K⁻¹)	0.11	−0.21	0.07	0.30	−0.35

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表 4 数值模拟结果

Table 4. Numerical Simulation Results

通道类型	质量流量/ (kg·s⁻¹)	出口平均流速/(m·s⁻¹)	出口平均温度/K	出口最大温度/K	出口最小温度/K
三角形	0.047	0.93	852.3	903.5	835.1
梅花形	0.091	0.44	852.1	957.8	827.1

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参考文献(16)

[1]	SIDDIQI A A. Beyond earth: a chronicle of deep space exploration, 1958-2016[M]. Washington: NASA, 2018: 341.
[2]	何宇豪,孟涛,卢瑞博,等. 空间核反应堆电源研究进展[J]. 上海航天,2019, 36(6): 126-133. doi: 10.19328/j.cnki.1006-1630.2019.06.018
[3]	POSTON D I, GIBSON M A, GODFROY T, et al. KRUSTY reactor design[J]. Nuclear Technology, 2020, 206(S1): S13-S30.
[4]	POSTON D I, GIBSON M A, SANCHEZ R G, et al. Results of the KRUSTY nuclear system test[J]. Nuclear Technology, 2020, 206(S1): S89-S117.
[5]	ZAKIROV V, PAVSHOOK V. Feasibility of the recent Russian nuclear electric propulsion concept: 2010[J]. Nuclear Engineering and Design, 2011, 241(5): 1529-1537. doi: 10.1016/j.nucengdes.2011.02.010
[6]	葛攀和,郭键,高剑,等. 星表核反应堆电源系统热工概念设计[J]. 载人航天,2017, 23(6): 784-789. doi: 10.3969/j.issn.1674-5825.2017.06.012
[7]	刘凯旋,张威震,解家春,等. 100kWe月面核电站方案研究[J]. 上海航天(中英文),2020, 37(2): 124-129.
[8]	DENG Y B, QIU B W, LU K L, et al. Performance evaluation and efficiency enhancement of a space thermionic fuel element for thermal energy conversion and utilization[J]. Applied Thermal Engineering, 2020, 173: 115237. doi: 10.1016/j.applthermaleng.2020.115237
[9]	STANCULESCU A. The role of nuclear power and nuclear propulsion in the peaceful exploration of space[M]. Vienna: International Atomic Energy Agency, 2005.
[10]	NIKITIN V P, OGLOBLIN B G, LUTOV Y I, et al. Program on the TOPAZ‐2 system preparation for flight tests[J]. AIP Conference Proceedings, 1993, 271(2): 741-746.
[11]	BENKE S M. Operational testing and thermal modeling of a TOPAZ-II single-cell thermionic fuel element test stand[J]. AIP Conference Proceedings, 1995, 324(1): 495-501.
[12]	钟武烨,赵守智,郑剑平,等. 空间热离子能量转换技术发展综述[J]. 深空探测学报,2020, 7(1): 47-60. doi: 10.15982/j.issn.2095-7777.2020.20200114001
[13]	NIKOLAEV Y V, KUCHEROV R Y, ERYOMIN S A, et al. Conductively coupled multi-cell TFE with electric heating pretest ability[J]. AIP Conference Proceedings, 1998, 420(1): 318-323.
[14]	STRECKERT H, BEGG L, PELESSONE D. Design of conductively coupled multi-cell thermionic fuel element[J]. AIP Conference Proceedings, 1999, 458(1): 1458-1463.
[15]	MARTINEZ M, STRECKERT H, IZHVANOV O, et al. Development and testing of a conductively coupled three cell thermionic converter[C]//1st International Energy Conversion Engineering Conference (IECEC). Portsmouth: American Institute of Aeronautics and Astronautics, 2003.
[16]	李东,李平岐,王珏,等. “长征五号”系列运载火箭总体方案与关键技术[J]. 深空探测学报(中英文),2021, 8(4): 335-343.