火箭推进

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%。

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.

引言
1 RBCC发动机构型及计算模型
2 一维计算与试验结果对比
3 发动机热力循环分析
4 发动机推力增益分析
5 结论

表1 发动机试验工况<br/>Tab.1 Working conditions of engine scramjet mode

表1 发动机试验工况
Tab.1 Working conditions of engine scramjet mode

表2 火箭推力室工作参数<br/>Tab.2 Working parameters of rocket thrust chamber

表2 火箭推力室工作参数
Tab.2 Working parameters of rocket thrust chamber

图1 发动机沿程压力分布<br/>Fig.1 Pressure distribution of the engine

图1 发动机沿程压力分布
Fig.1 Pressure distribution of the engine

图2 发动机沿程参数分布<br/>Fig.2 Parameters distribution of the engine

图2 发动机沿程参数分布
Fig.2 Parameters distribution of the engine

图3 发动机推力结果对比<br/>Fig.3 Thrust of the engine

图3 发动机推力结果对比
Fig.3 Thrust of the engine

图4 发动机热力循环<br/>Fig.4 Thermodynamics cycle of the engine

图4 发动机热力循环
Fig.4 Thermodynamics cycle of the engine

图5 发动机工作效率<br/>Fig.5 Working efficiency of the engine

图5 发动机工作效率
Fig.5 Working efficiency of the engine

图6 发动机有效能分布<br/>Fig.6 Exergy distribution of the engine

图6 发动机有效能分布
Fig.6 Exergy distribution of the engine

图7 发动机有效能占比<br/>Fig.7 The energy proportion of the engine

图7 发动机有效能占比
Fig.7 The energy proportion of the engine

图8 火箭推力室羽流虚拟流管<br/>Fig.8 Virtual flow tube for plume of rocket thrust chamber

图8 火箭推力室羽流虚拟流管
Fig.8 Virtual flow tube for plume of rocket thrust chamber

[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
[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.
[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.
[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.

备注

引言

1 RBCC发动机构型及计算模型

2 一维计算与试验结果对比

3 发动机热力循环分析

4 发动机推力增益分析

5 结论

期刊信息