Film cooling is often used to cool the turbine components and parts so that the threat of high heat transfer can be minimised significantly to prevent sudden seizure or failure of part. In this study, the effectiveness of the high issuing film cooling jets at the mid passage of the cascade is investigated. Bleed slots are placed at the leading edge to mimic the cavity between the combustor and first stage turbine arrangements. One geometrical passage of the cascade is modelled and Numerical data are obtained through the employment of the commercial CFD software, CD-Adapco StarCCM+. Menter shear stress transport turbulence (SST) k-w turbulence model in the flow solver are used for the research. The results of the non-dimensional temperature show that heat augmentation reduces significantly. The averaged total pressure loss seems to increase at the trailing edge due to the high energy input of the film flow and the interaction of the flow with the endwall. In general, the coefficient of the total pressure loss shows local creation of the pressure loss around the pressure side of the trailing edge. This implies that the blowing ratio must be controlled and checked for optimum performance.