航天推进技术研究院主办
[1]张留欢,杜泉,张蒙正.RBCC发动机火箭-冲压模态理想热力循环优化分析[J].火箭推进,2016,42(03):21-25.
ZHANG Liuhuan,DU Quan,ZHANG Mengzheng.Optimum analysis on ideal thermodynamic cycle of RBCC engine at special rocket-ramjet mode[J].Journal of Rocket Propulsion,2016,42(03):21-25.
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ZHANG Liuhuan,DU Quan,ZHANG Mengzheng.Optimum analysis on ideal thermodynamic cycle of RBCC engine at special rocket-ramjet mode[J].Journal of Rocket Propulsion,2016,42(03):21-25.
RBCC发动机火箭-冲压模态理想热力循环优化分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
42
期数:
2016年03期
页码:
21-25
栏目:
研究与设计
出版日期:
2016-06-30
- Title:
- Optimum analysis on ideal thermodynamic cycle of RBCC engine at special rocket-ramjet mode
- Keywords:
- RBCC; rocket-ramjet mode; ideal thermodynamic cycle; optimum analysis
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 基于RBCC发动机工作原理,开展了特定燃烧组织模式下,RBCC发动机火箭-冲压模态的理想热力循环优化分析.根据火箭-冲压模态发动机工作特点,建立了工质热力循环过程模型,计算获得了最佳压缩点温度及其对应的最佳压缩比、最大循环功、热效率等参数.同时,给出了燃烧室最高温度、空燃比对最佳压缩比、最大循环功和热效率的影响规律,以及RBCC发动机热力循环的优化方向.研究结果表明,通过提高一级燃烧室最高温度、降低引射比、调整进气道压缩比至最佳压缩比等措施均可有效提高RBCC发动机最大循环功及循环效率.
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备注/Memo
国家863项目
更新日期/Last Update:
1900-01-01