摘要
在实际叶片排几何模型不变的条件下,采用交接面周期性处理方法可大大缩小非定常流计算域,减小计算量,但该处理方法会给非定常流计算带来一些近似,通过某跨声速涡轮级三维粘流数值计算,分析和评估计算方法,结论是该方法不改变时间平均下的稳态性能参数,而且可用于多级涡轮非定常流计算.
The real blade-to-blade passage geometry can be computed owing to approximate treatment of the flow continuity condition on periodic boundaries.This technique is specifically intended to reduce the computational domain.The boundary treatment induces some approximate computation of the unsteady flow phenomena.These were analyzed in the cases of the E3 high-pressure turbine in which the viscous flow was computed.The main conclusion is that,this approach doesn t affect the time average performance parameters a...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第5期1066-1070,共5页
Journal of Aerospace Power
关键词
E3高压涡轮级
非定常流计算
交接面缩放
多级涡轮
性能参数
E3 high-pressure turbine
unsteady flow simulation
interface contraction/dilatation
multi-stage turbines
performance parameters
