摘要
用数值模拟的方法对旋流数、文氏管间距、扩压器与头部的间距等多点喷射燃烧室设计中的关键参数进行研究,来获取它们对多点喷射燃烧室回流区的影响规律.结果表明:旋流数由0.82提高到1.24,回流区最大负速度和长度分别增加了52%和34%,最大负速度随旋流器叶片安装角是线性变化的;文氏管间距由0增加到0.4倍的文氏管出口直径时,回流区半径增加了33%,长度增加了43%;增大扩压器出口面积和头部与扩压器间距有利于旋流器之间流量分配均匀.
A numerical investigation was conducted to study some key parameters of multi-injection combustor,including swirl numbers,space between venturis,distance between the dome and the diffuser.The influence law of these parameters on the multi-injection combustor＇s recirculation zone was concluded.This shows that,with increase of the swirl number,the reverse velocity of the recirculation zone will rise.When the swirl number increases from 0.82 to 1.24,the maximal reverse velocity is 52% greater and the recirculation zone is 34% longer.When the space between venturis changes from 0 to 0.4 times the exit diameter of venture,the radii of recirculation zone is 33% bigger and the length is 43% larger.With the increasing area of inlet of the diffuser and the growing distance between the dome and the diffuser,the distribution of the flow is more uniform.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第7期1536-1544,共9页
Journal of Aerospace Power
关键词
多点喷射燃烧室
燃气涡轮燃烧室
冷态流场
旋流数
数值模拟
multi-injection combustor
gas turbine combustor
cold flow field
swirl number
numerical simulation
