The turbine blade tip is one of the most vulnerable parts of thermal failures due to high temperature flow conditions. A more effective cooling method has been needed to prevent thermal failures of the turbine blade tip. In this study, slot cooling with the camberline rib at the blade tip is presented as an advanced and effective cooling method. The film cooling effectiveness (FCE) and flow characteristics of the turbine blade tip were investigated for Suction side Slot cooling (SS cooling) and Suction side Slot + Camberline Slot cooling (SS+CS cooling) using a commercial numerical analysis program. Validation was performed with the experimental results by comparing the pressure coefficients. The Reynolds number based on the axial chord length and the inlet velocity was set at 10,000. The tip clearance was varied from 1% to 3% of the blade span and the coolant mass flow rate fixed at 0.5% of the main flow. The SS+CS cooling showed highly enhanced cooling performance especially at the pressure side of the blade tip surface due to the insulating effect of the coolant from the camberline slot. The slot cooling in the blade tip, especially SS+CS cooling is expected to improve the thermal durability and reliability of the turbine blade tip with better insulating effect and coolant coverage.