改进型一体化加力燃烧室方案的数值模拟  

Numerical simulation on improved integrated afterburner scheme

作　　者：王伟龙[1] 金捷[1] 井文明 刘邓欢 季鹤鸣[2] 游庆江[2] 李江宁[2] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]z国航空工业集团公司沈阳发动机设计研究所,沈阳110015

出　　处：《航空动力学报》2015年第5期1119-1124,共6页Journal of Aerospace Power

摘　　要：针对传统加力燃烧室质量过大与非加力状态下流动损失巨大的问题展开了设计研究,提出了一种改进型一体化加力燃烧室方案,取消了常规的钝体稳定器,采用了内突扩中心锥的火焰稳定结构.采用了数值模拟的方法研究方案的性能.结果表明:该方案对入口参数不敏感;在所有研究的工况条件下,3种方案总压恢复系数均高于0.96,加力燃烧室的效率接近0.90;采用波瓣混合器的方案具有最佳的总体性能.An improved integrated afterburner scheme was proposed to solve the prob- lem of too large mass of traditional afterburner and too significant flow loss in non-augmenta- tion condition. This scheme canceled the conventional stabilizer of blunt body, and a sudden expanding structure of central cone for stabilizing the flame was adopted. Numerical simula- tion was conducted to research its performance. The result indicates that the scheme is not sensitive to inlet parameters total pressure recovery coefficients of three schemes on all ca- ses are greater than 0.96; afterburner efficiency is close to 0.90; the scheme with lobed mix- er has the best overall performance.

关 键 词：一体化 加力燃烧室 波瓣混合器 燃烧效率 总体性能 

分 类 号：V232.5[航空宇航科学与技术—航空宇航推进理论与工程]