Performance Analysis of Dual Mode Nuclear Thermal Propulsion System Based on SCO2 Brayton Cycle

被引：0

作者：

Liu X. ^{[1
,2
]}

Zhang H. ^{[1
]}

Yin D. ^{[1
]}

Chai X. ^{[2
]}

Zhang X. ^{[1
]}

机构：

[1] School of Energy Science and Engineering, Harbin Institute of Technology, Harbin

[2] Nuclear Power Institute of China, Chengdu

来源：

Hedongli Gongcheng/Nuclear Power Engineering | 2020年 / 41卷

关键词：

Dual mode nuclear thermal propulsion; Exergy efficiency; SCO[!sub]2[!/sub] Brayton cycle; Thermal efficiency;

D O I：

10.13832/j.jnpe.2020.S2.0102

中图分类号：

学科分类号：

摘要：

Dual-mode nuclear thermal propulsion system is an ideal power conversion system for future aerospace activities with both propulsion and power generation functions. In order to explore the coupling performance of the coupling of nuclear thermal propulsion system and the Brayton thermoelectric conversion module, based on the simple regenerative Brayton cycle, a nuclear thermal propulsion system is established, and a dual mode of propulsion module and power module is calculated and analyzed. The effect of cycle boost ratio, temperature rise ratio and compressor inlet temperature on the system thermal efficiency and exergy efficiency under power generation condition is studied. The results show that for the purpose of Mars exploration, the thrust and specific impulse meet the power requirements. The supercritical carbon dioxide (SCO2) Brayton cycle is used as the system of the power generation module to analyze its performance. The cycle thermal efficiency is 32% and the exergy efficiency is 53% under the given parameters, which provides a reference for further analysis. © 2020, Editorial Board of Journal of Nuclear Power Engineering. All right reserved.

引用

页码：102 / 107

页数：5

共 15 条

[1] pp. 158-209, (2016)
[2] BEVERIDGE J H., Feasibility of using a nuclear rocket engine for electrical power generation, AIAA/SAE 7th Propulsion Joint Specialists Conference, (1971)
[3] GRIMM T, HAMKE R., NERVA derived engine and operations concept, pp. 2006-4557, (2006)
[4] HASLETT R A., Space nuclear thermal propulsion program final report: PL-TR-95-1064, (1995)
[5] DRAKE B G, HOFFMAN S J, BEATY D W., Human exploration of Mars, design reference architecture 5.0: NASA-SP-2009-566, United States: IEEE Aerospace Conference Proceedings, (2010)
[6] CLOUGH J., Integrated propulsion and power modeling for bimodal nuclear thermal rockets, AIAA/ASME/ SAE/ASEE Joint Propulsion Conference & Exhibit, (2007)
[7] NAM S H, VENNERI P, KIM Y, Et al., Innovative concept for an ultra-small nuclear thermal rocket utilizing a new moderated reactor, Nuclear Engineering and Technology, 47, 6, pp. 678-699, (2015)
[8] pp. 45-76, (2018)
[9] JOSHUA A. C, TYAN P S, MARK J L, Et al., Integrated propulsion and power modeling for bimodal nuclear thermal rockets: AIAA 2007-5623, (2007)
[10] (2006)

← 1 2 →