This is Part Three of a four-part paper. It begins with Section 11.0 and continues to describe the comprehensive experiments and computational analyses that have led to a detailed picture of boundary layer development on airfoil surfaces in multistage turbomachinery. In this part, we present the experimental evidence that we used to construct the composite picture for LP turbines that was given in the discussion in Section 5.0 of Part 1. We present and interpret the data from the surface hot-film gages and the boundary layer surveys for the baseline operating condition. We then show how this picture changes with variations in Reynolds number, airfoil loading, and nozzle–nozzle clocking.
Boundary Layer Development in Axial Compressors and Turbines: Part 3 of 4— LP Turbines
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Halstead, D. E., Wisler, D. C., Okiishi, T. H., Walker, G. J., Hodson, H. P., and Shin, H. (April 1, 1997). "Boundary Layer Development in Axial Compressors and Turbines: Part 3 of 4— LP Turbines." ASME. J. Turbomach. April 1997; 119(2): 225–237. https://doi.org/10.1115/1.2841105
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