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Three-dimensional solutions of the Navier-Stokes equations for a turbine blade with a turning angle of 180 degrees have been computed, including blade tip treatments involving cavities. The geometry approximates Pratt&Whitney's preliminary design for the GGOT (Generic Gas Oxidizer Turbine). The data presented here will be used as a means of comparison for experimental data to be obtained from a linear cascade being built and tested at The University of Alabama, using the original GGOT blades. Results have been computed for a blade with 1% clearance, based on chord, and three different cavity sizes. All tests were conducted at a Reynolds number of 4x107/m. The grid contains 39,440 points with 10 spanwise planes in the tip clearance region of 5.008E-04 m. Streamline plots and velocity vectors, together with velocity divergence plots reveal the general flow behavior in the clearance region.