同轴双剪切气-气喷嘴数值模拟  

Numerical simulation of shear dual-coaxial gas-gas injector

作　　者：杜正刚[1] 高玉闪[1] 李茂[1] 金平[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2010年第4期829-834,共6页Journal of Aerospace Power

基　　金：国家863基金

摘　　要：通过求解k-ε湍流模型的Navier-Stokes方程组,对以气氢/气氧为推进剂的同轴双剪切喷嘴燃烧室流场进行数值模拟研究.结果表明:气-气推进剂在燃烧室内形成两个燃烧面,能在大流量下实现较高的燃烧效率;同轴双剪切喷嘴的氧喷注速度和氢氧速度比是同轴双剪切喷嘴设计的关键参数,氧喷注速度越小使推进剂的燃烧位置越远离喷注面,而氢氧速度比越大使燃烧位置越靠前;与气-液同轴剪切喷嘴相比,同轴双剪切气-气喷嘴的设计可以取较大的氧喷注速度和适合的氢氧速度比.The turbulent Navier-Stokes equations in combination with two equation k-ε turbulence models were used to simulate the flow field of shear dual-coaxial single element GO2/GH2 injector chamber.The results show that： the shear dual-coaxial injector has two shear combustion surfaces,enabling to achieve a high combustion efficiency at the condition of large mass flowrate,the oxygen injection velocity and the velocity ratio of hydrogen to oxygen are key parameters for shear dual-coaxial injector design,a lower oxygen injection velocity makes the combustion location far away from the faceplate,while a higher velocity ratio makes the combustion location closer to the faceplate.Compared with the gas-liquid shear coaxial injector,a faster oxygen injection velocity and proper velocity ratio of hydrogen to oxygen are preferable choice for design of shear dual-coaxial injector.

关 键 词：数值模拟 NAVIER-STOKES方程组 气-气喷嘴 流量 

分 类 号：V434.13[航空宇航科学与技术—航空宇航推进理论与工程]