There are many teat transfer augmentation arthods that are employed in turbine blade &sign, such as impingement cooling, film cooling, serpentine passages, trip strips, vortex chambers, and pin fins. The use of crorspins in the trailing edge ection of turbine blades is commonly a viable option due to their ability to promote turbulence as well supply structural integrity and stiffness to the blade itself. Numerous crosspin shapes and arrangements are possible, but mly certain configurations offer tigh Mat transfer capability while maintaining low total pressure loss. This gudy presents results from 3-D numerical simulations of airflow through a turbine Made internal cooling passage. The simulations model viscous flow and heat transfer over fill crosspins of circular cross-section with fixed Iright-todameter ratio of as, fixed transverse-to-diameter spacing ratio of 1.5, and varying streamwise spacing. Preliminary analysis indicates that enthrall effects dominate the flow and heat transfer at bwer Reynolds numbers. The flow dynamics involved with the relative dose proximity d. the endwalls for arch short crosspins have a definite influence co crosspin efficiency for downstream rows.