论文标题
低压涡轮级联的大型涡流模拟具有湍流端壁边界层
Large eddy simulation of a low pressure turbine cascade with turbulent end wall boundary layers
论文作者
论文摘要
我们介绍了MTU T161低压涡轮机的隐式大型涡流模拟，雷诺数为90,000，MACH数为0.6，均基于等级不连续的Galerkin方法。目的是验证有关可用实验数据的数值设置。我们讨论以端壁边界层厚度和自由流湍流强度来创建现实的流入边界条件所采取的步骤。这是通过根据基于傅立叶串联的合成湍流发生器来调整雷诺应力和湍流长度尺度的输入分布来实现的。中跨的刀片载荷和总压力损失都与测量值相吻合。在简短讨论了由于传入边界层和涡轮刀片的相互作用而出现的二次流结构后，我们表明该模拟还能够在整个通道高度上重现刀片后面的损失分布。
We present first results of an implicit large eddy simulation of the MTU T161 low pressure turbine at a Reynolds number of 90,000 and Mach number of 0.6, both based on isentropic exit conditions, using a high order discontinuous Galerkin method. The aim is to validate the numerical setup with respect to available experimental data. We discuss the steps taken to create realistic inflow boundary conditions in terms of end wall boundary layer thickness and free stream turbulence intensity. This is achieved by tailoring the input distribution of Reynolds stresses and turbulent length scale to a Fourier series based synthetic turbulence generator. Both blade loading and total pressure losses at midspan show excellent agreement with the measurements. Following a short discussion of the secondary flow structures emerging due to the interaction of the incoming boundary layer and the turbine blade, we show that this simulation is also able to reproduce loss distribution behind the blade over the whole channel height.
