航天器核动力推进系统热力学性能研究  

Study on Thermodynamic Performance of Nuclear Power Propulsion System in Spacecraft

作　　者：冯致远[1] 张昊春[1] 吉宇[2] 程献伟[1] 赵广播[1] FENG Zhiyuan;ZHANG Haochun;JI Yu;CHENG Xianwei;ZHA0 Guangbo(School of Energy Science and Engineering Harbin Institute of Technology, Harbin 150001, China;Institute of Nuclear and New Energy Technology Tsinghua University, Beijing 100084, China)

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001 [2]清华大学核能与新能源技术研究院,北京100084

出　　处：《载人航天》2016年第6期797-804,共8页Manned Spaceflight

基　　金：国家自然科学基金委创新研究群体(51421063);国家自然科学基金(51536001)

摘　　要：作为未来航天能源重要候选的以C02为工质的布雷顿循环空间核动力系统，目前在热力循环分析的研究方面有待深入。以钠冷快堆超临界C02布雷顿循环作为分析对象,针对不同工质最高循环温度下的循环效率以及不同的增压比和低温回热器冷端温差对循环效率的影响进行了研究。通过建立C02实际气体的RK方程和焓表达式，得出了输出功率随增压比的变化规律。研究结果表明提高循环最高温度和增压比均能有效提升循环效率，但提高增压比将影响回热器的回热效果，而较低的增压比会使高温回热器热负荷显著增加，合适增压比范围为3.0~3.2。As a promising proposal for the future space exploration,Brayton cycle space nuclear power system,which uses super critical CO_2 as the working fluid,is still lack of the thermodynamic analysis up to now. Therefore,the super-critical CO_2 Brayton cycle with sodium cooled fast reactor was studied. The effects of the highest temperature in cycle,the pressure ratio and the temperature difference of the cooler-side of low temperature recuperator(LTR) on cycle efficiency were discussed. The law of output power varying with the pressure ratio was obtained by building the expression of CO_2 real gas enthalpy and RK equation during the analysis process. The study results showed that the cycle efficiency could increase effectively by improving the highest cycle temperature or pressure ratio. But,the heat transfer condition deteriorated with the raised pressure ratio. While low pressure ratio could lead to high heat load of the high temperature recuperator. Thus,the suitable scope of pressure ratio is 3. 0 ~ 3. 2.

关 键 词：闭式布雷顿循环 超临界CO2 RK方程 增压比 

分 类 号：V439.5[航空宇航科学与技术—航空宇航推进理论与工程]