液体火箭发动机单喷注器燃烧室声学特性模拟实验原理及实现  

Principle and design of simulation test for acoustic charac-teristics of liquid rocket engine chamber with a single injector

作　　者：张蒙正[1] 张志涛[2] 郁锋[2] 汪亮[1] 

机构地区：[1]西北工业大学,西安710072 [2]西安航天动力研究所,西安710100

出　　处：《声学技术》2007年第2期268-272,共5页Technical Acoustics

摘　　要：依据相似理论,研究了高压补燃循环液体火箭发动机单喷注器燃烧室声学特性模拟实验的原理,建立了模拟实验系统,研究了实验方法,进行了某型高压补燃循环液体火箭发动机燃烧室和喷注器的声学特性实验。结果表明:模拟实验技术可行,实验方法正确,模拟实验结果为发动机设计提供了依据。According to the similarity theory, the principle and method of acoustic characteristics simulation test of liquid rocket engine chamber with a single injector were studied, and a test system was set up. The acoustic characteristics simulation test of the stage combustion cycle liquid rocket engine simulation chamber with a single injector was also conducted. The test results show that the technology and method of simulation test are correct and available. And the results of simulation test have served in the engine design.

关 键 词：液体火箭发动机 燃烧室 声学特性 模拟实验 

分 类 号：TB556[理学—物理]