航天推进技术研究院主办
[1]王 壮,李钰航,张蒙正,等.RBCC发动机不同构型隔离段流场仿真[J].火箭推进,2023,49(06):82-89.
WANG Zhuang,LI Yuhang,ZHANG Mengzheng,et al.Simulation on flow field in isolator of RBCC engine with different configurations[J].Journal of Rocket Propulsion,2023,49(06):82-89.
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WANG Zhuang,LI Yuhang,ZHANG Mengzheng,et al.Simulation on flow field in isolator of RBCC engine with different configurations[J].Journal of Rocket Propulsion,2023,49(06):82-89.
RBCC发动机不同构型隔离段流场仿真
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年06期
页码:
82-89
栏目:
目次
出版日期:
2023-12-25
- Title:
- Simulation on flow field in isolator of RBCC engine with different configurations
- 文章编号:
- 1672-9374(2023)06-0082-08
- 分类号:
- V435
- 文献标志码:
- A
- 摘要:
- 为探究椭圆微扩和异形变截面这两种结构隔离段对RBCC发动机推力性能的影响,以某构型RBCC发动机试验件为研究对象,对比了地面试验与数值模拟发动机下壁面中心线上的静压分布,验证了数值模拟结果的准确性。在来流马赫数为3、余气系数为1.5的工况下,通过数值模拟对两种隔离段构型下RBCC发动机燃烧室内的流动燃烧过程及发动机的推力性能进行了对比分析。结果表明:异形变截面隔离段的抗反压性能明显低于椭圆微扩隔离段; 当燃料释热较为集中,燃烧室内压升比相对较大时,异形变截面隔离段的下壁面处会产生较大的流动分离区,且一直向下游延伸,进入燃烧室,使得燃烧室入口的流场均匀性较差,从而降低发动机的推力性能。
- Abstract:
- To explore the impact of elliptical slightly-expanded isolator and square to circular variable cross-section isolator on the thrust performance of RBCC engine, a RBCC test piece with a certain configuration was taken as the research object.The accuracy of the numerical scheme is verified by comparing the static pressure distribution on the centerline of the lower wall between the experimental results and the numerical simulation results, and it shows the numerical scheme is reliable.When the inlet flow Mach number is 3, the excess air coefficient is 1.5, the flow field and combustion process structure of the two different RBCC isolators are analyzed, as well as the thrust performance of the engine.The results show that the anti-backpressure ability of variable cross-section isolator is significantly lower than that of elliptical slightly-expanded isolator.And when the heat release from the fuel is relatively concentrated and the pressure in the combustion chamber increases relatively large, a large flow separation zone will be generated at the lower wall of variable cross-section isolator, which extends to the downstream.And it will make the flow field uniformity of the chamber worse, which will result in the poor thrust performance.
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备注/Memo
收稿日期:2023-02-28; 修回日期:2023-04-01
基金项目:国家重点实验室基金(6142704220204)
作者简介:王壮(1995—),男,硕士,研究领域为液体火箭发动机流动、传热与燃烧。
更新日期/Last Update:
1900-01-01