固体火箭发动机潜入和非潜入喷管内流场模拟及对比  

Simulation and comparison of internal flow fields in solid rocket motors with submerged and nonsubmerged nozzle

作　　者：魏超[1] 侯晓[1] 李岩芳[1] 

机构地区：[1]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2005年第4期244-248,共5页Journal of Solid Rocket Technology

摘　　要：利用FLUENT流场计算软件,对采用潜入和非潜入喷管的全尺寸固体发动机,采用二维轴对称模型和准定常方法进行了内流场模拟计算和对比分析。结果表明,喷管潜入结构可有效地降低发动机后封头壁面附近的燃气速度,从而比非潜入发动机有更好的热防护环境;两种发动机在燃烧室内压强、速度和温度分布大致相同,非潜入喷管发动机在喷管出口轴线处燃气速度比潜入喷管发动机的大,而温度和压强较低。Based on FLUENT flow field calculation software, internal flow fields of full-size motors with submerged nozzle and nonsubmerged nozzle were simulatively calculated and compared by using 2D axisymmetric model and quasi-steady method. The results show that the configuration of submerged nozzle can effectively reduce gas velocity near the aft-dome case, and has better heat security environment. Pressure, velocity and temperature distributions in the chamber of both motors are approximately same. Gas velocity in outlet of the nonsubmerged nozzle motor is higher than that of the submerged nozzle motor,but gas temperature and pressure are lower.

关 键 词：固体推进剂火箭发动机 内流场模拟 潜入喷管 非潜入喷管 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]