关键词: 火箭推进剂喷嘴;离心喷嘴;流量系数;流量测量

Abstract: he problem of combustion instability under high mixture ratio has successfully solvedby using centrifugal injector with inlet mixing withdraw length and secondary injection in preburnerof a certain foreign LRE.The flow characteristics of injector affects the distributing-ratio of oxidizerand combustion instability.This paper has measured the flow characteristics of experiment injectorswith this structure, and given the effects of structure dimensions on flow characteristics.The resultsare important to learn the flow characteristics of injector with this structure and to design centrifugalinjectors.

Key words: Rocket propellant injector;Centrifugal injector;Flow coefficient;Flow ratemeasurement