The Effects of 3D Flow on Turbomachine Boundary Layers

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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.