在声学激发下,气液头火箭发动机中的短暂喷雾燃烧特性
Xuan Jin1,2, Chao Zhu3,4, Dejiang Chen5,6
1Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang, 621000, China. 1540445629@qq.com.
Scientific reports
|June 7, 2024
概括
这项研究模拟了液氧/气态甲喷头火箭发动机中的声学振荡. 横速干扰激发声学振荡,振幅受到激发和燃烧阶段的影响.
科学领域:
- 航空航天工程 航空航天工程
- 燃烧科学 燃烧科学
- 声学 声学 在声学方面
背景情况:
- 皮特尔火箭发动机对于太空推进至关重要.
- 了解燃烧不稳定性对于发动机的稳定性和性能至关重要.
- 气液火箭发动机中的声学振荡需要进一步研究.
研究的目的:
- 为了研究LOX/GCH4喷头火箭发动机中的声学振荡特征.
- 为了阐明从喷雾燃烧到燃烧器压力振荡的能量转移.
- 分析横速干扰对声响应的影响.
主要方法:
- 一个LOX/GCH4引擎的设计与一个矩形的燃烧器.
- 使用横速干扰模拟声响应.
- 研究刺激振幅对声响应的影响.
主要成果:
- 横向速度干扰成功激发了第一阶横向声学振荡.
- 确定了在外部刺激下维持声响应的机制.
- 燃烧器压力振荡幅度由激发幅度和热释放阶段主导.
- 时间平均燃烧器压力被横向速度干扰放大.
结论:
- 横速干扰是激发和研究声学振荡的有效方法.
- 这项研究提供了对平特发动机声响应机制的见解.
- 这些发现为实验性研究关于子级别皮特尔发动机声响应的研究提供了参考.
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