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对固体火箭发动机上由圆孔喷嘴喷入二次流所形成的气动喉部进行了三维数值模拟.考察了圆孔喷嘴形成气动喉部的典型三维流动特征和喷嘴流量特性.研究了不同喷嘴面积比、喷嘴个数、喷射角度、喷嘴构型及主要喷管参数对气动喉部调节喉部面积能力的影响.结果表明在相同的喷嘴面积比下,增加喷嘴个数、采用逆向喷射或选用收缩喷嘴构型都能显著提高气动喉部的扼流性能.
A three-dimensional numerical simulation of the aerodynamic throat formed by the injection of secondary flow through a circular orifice nozzle on a solid rocket motor was conducted. The typical three-dimensional flow characteristics of the aerodynamic throat formed by a circular orifice nozzle and the nozzle flow characteristics were investigated. The results show that under the same nozzle area ratio, the number of nozzles can be increased, the number of nozzles can be increased by reverse jetting or the shrinkage can be selected by the ratio of nozzle number, jetting angle, nozzle configuration and main nozzle parameters. Nozzle configuration can significantly improve the choke performance of pneumatic throat.