The Effects of 3D Flow on Turbomachine Boundary Layers

3D 流动对涡轮机边界层的影响

• 批准号: 2299849
• 金额: --
• 依托单位: University of Cambridge
• 依托单位国家: 英国
• 项目类别: Studentship
• 财政年份: 2019
• 资助国家: 英国
• 起止时间: 2019 至 无数据
• 项目状态: 已结题
• 来源: https://gtr.ukri.org/projects?ref=studentship-2299849
• 关键词: Effects; 3D; Flow; Turbomachine; Boundary

Blade surface losses are proportional to the dissipation coefficient multiplied by velocity cubed. In a two-dimensional turbulent boundary layer these losses are well understood and models exist to calculate the loss. However, in a blade passage, transverse pressure gradients result in three-dimensional boundary layers in which the losses are not well understood. This project aims to define the three-dimensional boundary layer seen in turbomachinery, quantify three-dimensionality of a boundary layer and measure the change in dissipation coefficient with three-dimensionality. The project also aims to understand the mechanisms behind any increased loss and to investigate whether 3D effects on boundary layers impact transition to turbulence. The dissipation coefficient of a 3D boundary layer has not been measured before and this project will measure this experimentally. The mechanisms of increased loss will be investigated using high fidelity computational fluid dynamics.

叶片表面损失与耗散系数乘以速度的立方成正比。在二维湍流边界层中，这些损失很好理解，并且存在计算损失的模型。然而，在叶片通道中，横向压力梯度会产生三维边界层，其中的损失尚不清楚。该项目旨在定义涡轮机械中的三维边界层，量化边界层的三维性并测量三维耗散系数的变化。该项目还旨在了解损失增加背后的机制，并研究边界层的 3D 效应是否会影响向湍流的过渡。以前从未测量过 3D 边界层的耗散系数，本项目将通过实验测量该系数。将使用高保真计算流体动力学研究损失增加的机制。