科研之友
微信
新浪微博
Facebook
分享链接
摘要
New generation military aero-combustor is high (FAR) (0.051 and above) combustor. It is stoichiometric direct mixing combustion. Fuel air module design configuration is proposed. New generation civil aero combustor is high pressure (such as pressure ratio 70 and above) low emissions combustor. Because of extremely short autoignition delay time, it cannot be premixed combustion, must be lean direct mixing (LDM) combustion. By combination of simple pressure swirl fuel nozzle and axial air swirler as basic fuel air combustion design, with the whole combustor the configuration, with fuel staging, the emissions are good without combustion instability problem. Both combustors use very high combustion air fraction, thus there is an idle lean blow out (LBO) issue. Design approaches to solve idle LBO problem are proposed for both type combustors. New liner cooling design is presented for outer liner and inner liner. The results of this study will provide guideline for the development of next generation aero combustors.
- 单位
