一、绪言 1979年东京大学宇宙航空研究所试制了供七吨推力氢氧发动机系统用的准飞行型燃气发生器,并进行了试验。这里作一扼要介绍。为了缩小体积和减轻重量,飞行用的燃气发生器一般多直接安装在涡轮喷嘴的集气环上。燃气发生器的基本问题是,在不烧毁燃气发生器反应室和涡轮叶片的情况下如何组织燃气混合问题。当然,这取决于反应室和喷注器的结构形式,但燃气发生器的有些问题并不完全符合 I. INTRODUCTION In 1979, the Institute of Aeronautics and Astronautics at the University of Tokyo trial-produced a pilot-type gas generator for a seven-ton thrust oxyhydrogen engine system and conducted tests. Make a brief introduction here. In order to reduce the size and weight, the flight gas generator is usually installed directly on the turbine nozzle ring. The basic issue with gas generators is how to organize gas mixing problems without burning down the gas generator chamber and turbine blades. Of course, this depends on the structure of the reaction chamber and the injector, but some problems with the gas generator do not exactly match