摘要
介绍了补燃循环液体火箭发动机燃烧室声学特性模拟实验原理、方法和在发动机高频燃烧不稳定性研究中的应用。模拟实验系统包括激励源、模拟燃烧室和声学特性测量系统等。激励源为扬声器或者喷嘴气流。模拟燃烧室是依据高频燃烧不稳定性特征设计、与实际燃烧室有相同固有频率的缩尺件。声学特性测量系统包括麦克风、频谱分析仪和示波器等。模拟实验主要用于研究特定燃烧室的声学特性，研究给定燃烧室结构下喷嘴和隔板的优化设计，研究高频燃烧不稳定性的机理。
The principle, test system, method and application of acoustic characteristic simulation test of the stage combustion liquid rocket engine chamber were introduced, The simulation test system includes the exciter, simulation chamber and acoustic characteristics measuring system. The exciter could select loudhailer or gas flow of injector. The simulation chamber was a reduced scale element which had the same natural frequency as the actual chamber＇ s, The simulation test was used to research the chamber acoustic characteristics and mechanism of high frequency combustion instability, also to optimize the design of injector and baffles configuration parameter for special chamber.
出处
《实验技术与管理》
CAS
2007年第8期39-42,共4页
Experimental Technology and Management
关键词
补燃循环
液体火箭发动机
高频燃烧不稳定性
声学特性
模拟实验
stage combustion
liquid rocket engine
instability of high frequency burning
acoustic characteristics
simulation test
