有冲击的受限通道内流场的数值仿真

Numerical Investigation of Flow Field in a Confined Channel with Impingement

采用数值模拟的方法对简化后的涡轮叶片冷气通道进行了数值模拟,着重研究端壁对有错排射流冲击的冷气通道的影响。结果表明:通道内的横流把射流推向下游并阻止其冲击到靶面,横流作用对通道下游流场有很大影响;射流的冲击反卷和诱导作用在射流两侧形成方向相反的漩涡,漩涡把靶面部分高速区卷到左右侧壁,甚至达到射流孔板附近,产生较大的速度梯度;上游横流作用使射流下游形成低速区,随着横流的发展低速区逐渐减小,并向射流孔板方向偏移。

Numerical simulation has been carried out to investigate the flow behaviors in the cooling channel of turbine blade. Particular attention has been paid to the effect of the confined wall of the cooling channel with staggered jets impingement. Important aspects of the study include ： the cross - flow in the channel pushes the jets and prevents them reaching target wall. This effect is more significant in the downstream region of the channel. Two counter - rotating vortices exist around the jets, and blow the flow with high velocity to the side walls and top wall of the channel. There is low - velocity region behind the jets, moving to the impingement plate as the development of the cross - flow and the area of the region decreases with increasing cross - flow velocity.