The boundary layer on the end wall of a turbine blade cascade is subject to cross-stream pressure gradients in the blade passage, which generate a cross-stream velocity component to make it three dimensional. This distorts the turbulence relative to a two-dimensional boundary layer and impacts the end wall heat transfer. This study presents measurements of the three-dimensional boundary layer in a turbine cascade obtained with a laser Doppler velocimeter. In addition, two types of Reynolds-averaged Navier–Stokes models are compared to the measurements: the Shear Stress Transport model using the isotropic eddy viscosity assumption and a Reynolds stress model that allows for anisotropy of the Reynolds stress. Neither model fully captures the complexity of the three-dimensional boundary layer in a turbine blade passage, particularly for turbulence associated with the cross-stream flow and for the highly accelerated three-dimensional boundary layer at the passage exit. Measurements at the passage exit indicate a very thin boundary layer with laminarlike qualities. Because of the boundary-layer complexity, end wall heat transfer is not well predicted toward the pressure side and the exit of the blade passage.
Three-Dimensional Boundary Layer in a Turbine Blade Passage
Journal of Propulsion and Power ; 33 , 4 ; 954-963
2017-01-19
10 pages
Article (Journal)
Electronic Resource
English
Three-Dimensional Boundary Layer in a Turbine Blade Passage
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