摘要
通过试验和数值模拟的方法研究了主燃孔几何参数与布局对双旋流燃烧室内三维冷热态流场的影响。用粒子图像测速仪(PIV)对不同工况的冷热态流场进行测量,用多点温度耙对燃烧室出口温度分布进行测量,用多点取样管和气体分析仪对燃烧室出口气体成分进行分析。用商业软件Fluent对不同主燃孔时的燃烧室冷热态流场进行数值模拟。计算结果与试验数据相当吻合,表明在相同的进口条件下,燃烧室主燃孔的几何参数和布局变化对燃烧室的冷热态流场、出口温度及燃气成分分布有较大的影响。
The effects of different primary holes geometric parameters and arrangements on three-dimensional flow fields of a dual swirl gas turbine combustor are investigated by the experiment and the nu- merical simulation. The cold and reacting flow fields in gas turbine combustor are measured by a two-dimensional particle image velocimetry （PIV） system. The radial profiles of the exit gas temperature are measured by multiple-point thermoelectric couple probe. The multiple-point gas sampling probe and the gas analyzer are used to measure radial distributions of the exit pollutants concentration. Three-dimensional flow fields are calculated by commercial software Fluent. Calculations are in fair agreement with the experimental data. Comparisons show that primary holes have considerable influences on flow fields and profiles of the outlet gas temperature and pollutant concentration with the same inlet condition.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2008年第1期26-31,共6页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
航空航天推进
流场
主燃孔
双旋流燃烧室
spacecraft propulsion
flow field
primary hole
dual swirl combustor
