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Abstract
Many experimental studies have been conducted until now to explore the details of aerodynamics and heat transfer inside the gas turbine engine. Due to limitations in the experimental facility, most of the experiments have been performed under non - realistic conditions such as low inlet / outlet pressure ratio, low inlet temperature, non rotating turbine blade which are far from the actual turbine operating condition. One of the most critical components of gas turbine engines, rotor blade tip, is exposed to high thermal loads. It is a significant challenge to the designer to protect the turbine material from this severe operating condition. Leakage flow over the blade tip is also one of the important issues to improve the turbine performance. High pressure gas turbine stage with real operating conditions was modelled and simulated using commercial CFD solver ANSYS FLUENT® 15.The modelled turbine stage has 46 vanes and 76 blades with a pressure ratio of 2.4 and a rotational speed of 12630 rpm. Depending on the validation, standard k-f model is employed; grid independency check exceeded 7.6 million elements