固体燃气涡轮火箭发动机掺混燃烧实验方法  

Experimental method of mixing and combustion in solid propellant air turbo rocket

作　　者：李江[1] 王伟[1] 刘洋[1] 刘诗昌[1] 杨昀[1] 杨飒[1] 

机构地区：[1]西北工业大学燃烧热结构和内流场重点实验室,西安710072

出　　处：《固体火箭技术》2013年第2期170-174,共5页Journal of Solid Rocket Technology

摘　　要：为研究固体燃气涡轮火箭发动机(SP-ATR)补燃室掺混燃烧规律,建立了一种采用多喉道喷管进行落压模拟的补燃室掺混燃烧实验方法,并利用该方法开展了典型工况下的地面直连实验研究,获取了流道内压强、温度分布、发动机推力等参数。结果表明,文中建立的补燃室掺混燃烧实验方法切实可行;两级喉道喷管可较好实现落压模拟功能;典型工况下补燃室燃烧效率、发动机性能较好;圆孔型掺混器流通面积较为合适,但对补燃室中段温度分布改善有限,为获得较优的发动机性能,还需进一步就掺混燃烧组织方式开展优化研究。The experimental method, which employs the multi-throat-nozzle as a decompression device to achieve befitting pres-sure, was derived, moreover, the ground direct-connect experiment of solid propellant air turbo rocket （SP-ATR） under typical operation modes was performed in order to investigate performances and the variation in the secondary chamber. The results show that the reliability of the proposed method to obtain parameters of mixing and combustion in SP-ATR can be demonstrated. The two-stage nozzle is designed and the decompression function is perfect. Combustion efficiency and engine performance are fairish. The flow cross-section area of mixing-enhanced device is appropriate, but round-hole shape doesnt play an important role in the temperature homogeneity. Moreover, the configuration of the combustion chamber and mixing-enhanced ways needs further optimal investigation to get better performance.

关 键 词：实验方法 掺混燃烧 固体燃气涡轮火箭发动机 多喉道喷管 掺混器 

分 类 号：V437[航空宇航科学与技术—航空宇航推进理论与工程]