摘要
为保证涡轮盘满足适航规章的安全性要求,采用单向FSI(fluid structure interaction)数值方法,研究旋转盘腔无量纲进气位置的变化对冷却效果的影响,并依据旋转盘腔冷却问题的工程评价体系对冷却效果进行评价.结果表明:无量纲进气位置的改变使旋转腔的流动结构发生变化,从而影响盘面换热效果和转盘的温度分布,导致与温度梯度紧密相关的热应力水平也发生变化.随着无量纲进气位置的提升,旋转盘腔的流阻损失增大,转盘迎风面的平均换热效果减弱,转盘的应力水平和在低半径处的最大等效应力值均下降.无量纲进气位置的变化能够从部件承受能力和实际使用载荷两方面对涡轮盘的失效概率产生影响.因此,在涡轮盘腔的设计阶段,需要考虑无量纲进气位置对涡轮盘安全性的影响.
Fluid structure interaction numerical method was applied to investigate the in-fluence of air inlet position on the cooling effect of the rotating cavity. And, in order to ensure the safety of the turbine disk, the cooling effect was evaluated by an engineering evalu ation system, which includes resistance evaluation, heat transfer evaluation and stress distribution evaluation. The results show that, the air inlet position has a great influence on the fluid structure in the rotating cavity, which determines the heat transfer and the temper- ature distribution of the rotating disk. Furthermore, the thermal stress of the rotating disk related to the temperature gradient can be affected. With the rise of the inlet position, the frictional windage of the rotating cavity increases, the heat transfer of the windward of the disk slacks, and the stress level and the maximum value decline. Therefore, the change of the inlet position has an effect on the failure probability of the turbine disk from two aspects： the material affordability and the working stress.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第8期1681-1687,共7页
Journal of Aerospace Power
基金
教育部长江学者创新团队"航空发动机复杂系统安全性"(IRT0905)
关键词
适航
旋转盘腔
进气位置
冷却效果
敏感性分析
airworthiness
rotating cavity
air inlet position
cooling effect
sensibility analysis
