As the efficiency of a gas turbine is proportional to the inlet temperature of the gas it is desirable to keep the inlet temperature of the gas as high as possible. However, the metallurgical limit restricts the maximum temperature of the gas that can be utilized. Modern gas turbine blades operate at highest possible gas temperatures through metallurgical means as well as effective cooling of the turbine blades. The trailing-edge of a gas turbine blade is quite thin and provides a converging channel for the passage of the coolant. Therefore, techniques such as impingement or film-cooling are difficult to deploy in this region. Instead, pin-fin cooling can be effectively used that also reinforces the blades to withstand the stresses. Pin-fin cooling can be modeled as flow over several small circular cylinders with an aspect ratio of unity that are placed in a perpendicular direction to the flow of the coolant. Due to the presence of multiple cylinders and the end-walls the flow of the coolant in this region is quite complex. To accurately characterize the flow and heat transfer characteristics in this complex flow field, an eddy-resolving method is needed. To this end, the present work aims to study the flow and heat transfer characteristics using large-eddy simulation. Large temperature differences, between the fin and the incoming flow, are considered that range from 25◦C to 300◦C. The effects of large temperature differences on the flow and thermal characteristics are studied both on the surface of the fins as well as in the near-wake. To begin with, non-isothermal flow over a single fin is analyzed following which a row of fins is considered. In future, this work will be extended to study non-isothermal flow over a matrix of fins placed in the converging section of a gas turbine trailing-edge.