Abstract: In order to obtain the design parameter of gelled propellant rocket engine chamber with high combustion efficiency, seven different geometry chambers were designed according to the property of propellant. The effects of combustion chamber characteristic length, impinging injector diameter and propellant viscosity on combustion efficiency were researched by the test method. The results indicate that the increase of chamber characteristic length could enhance residence time of propellant in chamber, and improve the atomization and combustion. Reducing the injection orifice diameter could increase the rate of shear, decrease propellant viscosity and improve combustion efficiency. In order to improve the combustion efficiency of gelled fuel containing carbon, the diameter of carbon particle should be decreased, or the chamber characteristic length should be increased.

Key words: Unlike double impinging injector； Characteristic length； Orifice diameter； Combustion efficiency

摘要： 为了获得凝胶推进剂火箭发动机高效燃烧室的设计参数,依据推进剂特性,设计了7种不同结构的燃烧室,通过实验手段,研究了燃烧室特征长度、喷嘴孔径和推进剂物性等参数对燃烧效率的影响。结果表明:增大燃烧室的特征长度,增加了推进剂的停留时间,有利于推进剂充分雾化和燃烧。减小撞击孔径,提高了射流的剪切速率,降低了推进剂的粘性,可以改善雾化和燃烧效率。为了提高含碳凝胶推进剂的燃烧效率,需减小碳粒粒度或者增加燃烧室特征长度。

关键词: 互击式喷嘴;特征长度;孔径;燃烧效率