液体火箭发动机气液同轴式喷嘴声学特性的实验研究

AN EXPERIMENTAL STUDY ON ACOUSTIC CHARACTERISTICS OF GAS-LIQUID COAXIAL INJECTOR OF LIQUID ROCKET ENGINE

关键词:  液体推进剂火箭发动机  火箭推进剂喷嘴  同轴射流  声学性质

Key words:  Liquid propellant rocket engine  Rocket propellant injector  Coaxial jet  Acoustic property

摘要:

对液体火箭发动机气液同轴式喷嘴声学特性进行了深入的实验研究，确定了不同缩进比的气液同轴式喷嘴工作时发生啸叫的参数范围、啸叫的频率和声压级分布，并考察了啸叫对喷嘴雾化特性的影响。结果表明；气液同轴式喷嘴的啸叫区间与喷嘴的结构尺寸有密切的关系．较大的喷嘴缩进比对啸叫有明显的抑制作用，啸叫的主要成分是高频噪声，这种喷嘴啸叫可能成为诱发发动机高频不稳定燃烧的重要因素。另外，实验还发现，在较低的气体喷注压降下，啸叫对喷嘴雾化有一定的强化作用。

Abstract:

he acoustic characteristics of gas-liquid coaxial injector of liquid rocket engine havebeen experimentally studied. The parameter zone of injector for whistler, the frequency of whistlerand the distribution of sound pressure degree were determined, and the effect of whistler on atomization was investigated. The results show that the whistler zone of injector mainly depends on the structure of injector. Increasing the indent ratio of injector can obviously restrain the whistler. The component of injector whistler is mainly high frequency noise and the frequency increases with the increaseof the pressure drop of gas injection. This kind of injector whistler in rocket engine may result in theunstable combustion, and under low pressure drop of gas injection, the whistler has obvious effect onatomization.