| 引用本文: | 崔朋,李清廉,成鹏,等.液氧甲烷膨胀循环变推力发动机系统方案对比研究.[J].国防科技大学学报,2020,42(3):106-115.[点击复制] |
| CUI Peng,LI Qinglian,CHENG Peng,et al.A comparative study of system schemes for LOX/LCH4 expander cycle liquid rocket engine[J].Journal of National University of Defense Technology,2020,42(3):106-115[点击复制] |
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| 液氧甲烷膨胀循环变推力发动机系统方案对比研究 |
| 崔朋1,2,李清廉1,2,成鹏1,2,张北辰1,2 |
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(1. 国防科技大学 空天科学学院, 湖南 长沙 410073;2. 国防科技大学 高超声速冲压发动机技术重点实验室, 湖南 长沙 410073)
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| 摘要: |
| 当前对液氧甲烷膨胀循环变推力火箭发动机的研制难点和关键技术认识不够清楚,尤其是在大变比推力调节方案方面。基于整个发动机系统,采用理论计算方法,探讨甲烷膨胀做功能力以及变推力调节方案可行性。分别给出了单涡轮系统方案和双涡轮系统方案,首次给出了不同工况下详细的系统状态参数分布,进行了对比分析,并探讨了甲烷做功能力随室压的变化规律。研究结果表明,甲烷做功能力随着室压的减小呈现先减小后增大的趋势,单涡轮和双涡轮系统方案均能够实现大范围推力调节；相比单涡轮方案,双涡轮方案能够更好地保证混合比,且甲烷气体做功能力利用效率更高,氧涡轮和燃料涡轮功率变化范围较窄,涡轮所处环境较为缓和,因此双涡轮系统方案具备一定优势。 |
| 关键词: 液氧甲烷 膨胀循环 变推力火箭发动机 单涡轮系统方案 双涡轮系统方案 对比研究 |
| DOI：10.11887/j.cn.202003014 |
| 投稿日期：2018-11-29 |
| 基金项目:国家自然科学基金资助项目(11472303,11402298)；国家重大基础研究专项资助项目(613239)；教育部新世纪优秀人才支持计划资助项目(NCET-13-0156) |
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| A comparative study of system schemes for LOX/LCH4 expander cycle liquid rocket engine |
| CUI Peng1,2, LI Qinglian1,2, CHENG Peng1,2, ZHANG Beichen1,2 |
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(1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;2. Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| The researches about the LOX/LCH4 expander cycle throttling liquid rocket engine are rare and its recognition of it is not distinct, especially at the system level. Based on the whole engine system, the theoretical method was adopted to investigate the work capacity of CH4 and the feasibility of throttling schemes. The single-turbine and double-turbine throttling schemes were given, and the detailed comparison between them was analyzed. The results reveal that CH4 work capacity decreases at first and then increases with the decrease of chamber pressure. And the proposed throttling schemes are feasible. Moreover, compared with the single-turbine scheme, the oxidizer and fuel mass flows can be adjusted respectively for double-turbine scheme and the mixture ratio can keep constant better. Meanwhile, the work capacity of CH4 for double-turbine scheme is much higher, the powers of the oxygen and fuel turbines vary in a narrow range, and the turbines work in a more relaxed environment. Therefore, considering the system reliability, the double-turbine scheme is advantageous to a certain extent. |
| Keywords: LOX/LCH4 expander cycle throttling liquid rocket engine single-turbine system scheme double-turbine system scheme comparative study |
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