The design of gas turbines requires an understanding of advanced cooling techniques, as hot components such as the combustor, nozzle, and blade are subjected to high thermal loads from combustion gas. These hot components may have gaps between them due to different levels of thermal expansion, and these gaps can cause misalignment. In this study, the film cooling effectiveness of the nozzle endwall with purge flow and film cooling hole arrangements was analyzed in the context of misalignment. The results showed that backward misalignment caused a significant change in the flow pattern on the endwall surface, with large step-induced vortices forming near the suction side and entering the nozzle passage. As a result, film cooling effectiveness was only high where the purge flows were gathered, and nearly absent on other surfaces. And the coolant flows from film cooling holes in the passage came out more straightly through the nozzle passage direction with the misalignment. So, the film cooling coolant affected further and narrow region. In contrast, coolant flows from film cooling holes without misalignment had compound angles and affected a shorter, wider region. In conclusion, these phenomena suggest that the effects of misalignment should be taken into account when designing the film cooling of gas turbine hot components, and that arranging film cooling holes along the pressure side of the airfoil may be more effective than upstream arrangements.