航天推进技术研究院主办
[1]南向军,李斌,何国强.RBCC发动机火箭及火箭冲压模态热力循环分析[J].火箭推进,2023,49(05):39-45.
NAN Xiangjun,LI Bin,HE Guoqiang.Thermodynamic cycle analysis of RBCC engine rocket and rocket-scramjet mode[J].Journal of Rocket Propulsion,2023,49(05):39-45.
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NAN Xiangjun,LI Bin,HE Guoqiang.Thermodynamic cycle analysis of RBCC engine rocket and rocket-scramjet mode[J].Journal of Rocket Propulsion,2023,49(05):39-45.
RBCC发动机火箭及火箭冲压模态热力循环分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年05期
页码:
39-45
栏目:
目次
出版日期:
2023-10-25
- Title:
- Thermodynamic cycle analysis of RBCC engine rocket and rocket-scramjet mode
- 文章编号:
- 1672-9374(2023)05-0039-07
- 分类号:
- V231
- 文献标志码:
- A
- 摘要:
- 为了研究RBCC发动机火箭模态及火箭冲压模态的工作特性,基于发动机地面自由射流试验结果,利用一维气动理论构建了发动机火箭及火箭冲压模态的性能分析模型,对发动机6 Ma来流条件的试验数据进行了处理,获得了发动机轴向的沿程气流参数,分析了发动机的热力循环、工作效率、有效能分布以及部件和排气中的有效能分配比例。结果表明:一维计算得到的推力与试验结果误差在5%以内; 火箭冲压模态下火箭燃气的引入可以有效提升发动机的热循环效率(约提升20%),火箭燃气的引入对有效能产生率和有效能的分配比例影响不大,火箭冲压和冲压模态的有效能产生率分别为0.45和0.48; 火箭模态推力增益产生的主要原因是火箭燃气的能量添加至冲压流道中,形成了有效的热力循环,产生了机械能增量,最终表现出推力增益,约为29%。
- Abstract:
- Based on the ground free-jet test results, a performance analysis model of rocket and rocket-scramjet mode of RBCC engine was established by using one-dimensional aerodynamics theory. Then the engine test data at Mach 6 was processed and the flow parameters along the engine axis were obtained, wihle the thermodynamic cycle, work efficiency, exergy distribution and exergy components of each part were analyzed. Results proves the high accuracy of the established energy calculation model, and the thrust error between 1-D calculation and test results is less than 5%. In rocket-scramjet mode, the introduction of rocket gas can effectively improve the thermal cycle efficiency of the engine by about 20%, while it has little effect on the exergy generation rate and effective energy distribution ratio. The main reason for a thrust gain of 29% under rocket mode is that the energy of rocket gas is added to the scramjet flow tube, which forms an effective thermal cycle in the scramjet flow tube and produces a certain mechanical energy increment.
参考文献/References:
[1] ODEGAARD E A,STROUP K E.Ejector ramjet engine tests:Phase I[R].AFAPL-TR-67-118.
[2] STROUP K E,PONTZER R W.Ejector ramjet system demonstration[R].AFAPL-TR-67-118.
[3] BULMAN M,NEILL T,YAM C.Strutjet RBCC engine performance[EB/OL].https://www.semanticscholar.org/paper/Strutjet-RBCC-Engine-Performance-Bulman-Neill/63c3
36d413ad4f0118b80594dfddc429b7fc0134,1999.
[4] 刘佩进.RBCC引射火箭模态性能与影响因素研究[D].西安:西北工业大学,2001.
[5] 刘佩进,何国强,陈剑,等.低速条件下引射火箭实验研究[J].固体火箭技术,2002,25(1):69-72.
[6] 王国辉,蔡体敏,何国强,等.火箭基组合循环发动机引射模态流动分析[J].推进技术,2002,23(4):298-302.
[7] 吕翔,何国强,刘佩进.RBCC引射模态准一维性能分析模型[J].推进技术,2006,27(6):529-531.
[8] 吕翔,何国强,刘佩进,等.RBCC火箭引射模态热力壅塞研究[J].航空动力学报,2008,23(3):563-568.
[9] 陈军,白菡尘.RBCC引射模态气流抵抗反压能力受掺混程度影响研究[J].推进技术,2022,43(4):37-45.
[10] 黄国庆.火箭基组合循环发动机引射模态性能研究[D].长沙:国防科学技术大学,2010.
[11] 刘洋,何国强,刘佩进,等.RBCC引射/亚燃模态过渡点选择[J].固体火箭技术,2009,32(5):500-505.
[12] 刘洋,何国强,刘佩进,等.RBCC引射/亚燃模态过渡工作过程数值模拟[J].推进技术,2009,30(6):641-646.
[13] 张建东,王占学,张蒙正,等.火箭冲压组合循环推进系统掺混参数研究[J].空气动力学学报,2010,28(2):222-225.
[14] 王亚军,何国强,潘科玮,等.RBCC亚燃模态热力喉道机理的数值模拟[J].推进技术,2013,34(7):932-937.
[15] 李梦磊,杨雪,杨一言,等.RBCC在模态转换过程中的内流场特性[J].火箭推进,2021,47(6):39-45.
LI M L,YANG X,YANG Y Y,et al.Research on internal flow field characteristics of RBCC during mode transition[J].Journal of Rocket Propulsion,2021,47(6):39-45.
[16] 吴亚可,刘继方,胡宗纯,等.基于亚燃RBCC构型的引射模态一次火箭节流策略研究[J].推进技术,2022,43(1):61-69.
[17] 刘昊,王春民.不同燃料RBCC发动机性能分析[J].火箭推进,2021,47(6):33-38.
LIU H,WANG C M.Analysis of RBCC engine performance with different fuel[J].Journal of Rocket Propulsion,2021,47(6):33-38.
[18] 南向军,李斌,何国强,等.RBCC发动机冲压模态热力循环分析[J].火箭推进,2022,48(6):17-25.
NAN X J,LI B,HE G Q,et al.Analysis on thermodynamic cycle of scramjet mode for RBCC engine[J].Journal of Rocket Propulsion,2022,48(6):17-25.
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备注/Memo
收稿日期:2022-03-15; 修回日期:2022-05-16
基金项目:国家重点项目
作者简介:南向军(1985—),男,博士,研究员,研究领域为火箭基组合循环发动机。
更新日期/Last Update:
1900-01-01