摘要
对某型燃气轮机涡轮过渡流道流场进行数值模拟,得到了与实验结果比较吻合的计算结果。结果表明:过渡段内流动为亚声速流动,沿流道有较大的逆压梯度,整流支板的作用类似于扩压叶栅。该方法与结果为此类过渡流道的设计提供了参考,并为以后的进一步改进和优化打下了坚实的基础。
The numerical simulation results of the transition duct flowfield correspond with the experimental data mostly.The results show that： air flow in the transition duct is subsonic,there is a large extent in adverse pressure gradient and the role of the strut fairing is similar to diffuser cascade.The numerical simulation approach and corresponding results have contributed substantially towards extending the database for designing such kind of transition duct and lay solid foundations for the transition duct improvement and optimization in the next step.
出处
《航空计算技术》
2012年第1期4-7,共4页
Aeronautical Computing Technique
基金
国家自然科学基金项目资助(51076131)
关键词
涡轮过渡流道
整流支板
亚声速流动
逆压梯度
数值模拟
transition duct
strut fairing
subsonic flow
adverse pressure gradient
numerical simulation
