Numerical Simulation of Heat Transfer and Flow Enhancement Through Multi-Row Film Holes for Gas Turbine Blade Cooling

To increase gas turbine power output and thermal efficiency, turbine inlet temperatures

can exceed the melting point of component materials. Blade cooling techniques are thus

required. This study reviews external cooling methods for gas turbine blade tips. Recent

publications on cooling technology improvements were analyzed to enhance turbine

blade cooling. The operating conditions and cooling requirements of turbine blades

were examined. Air was blown through a duct in the turbine blade at lower temperatures

to cool the blade by adjusting the air pressure to match internal pressures. The inlet air

pressure was 24,000 Pa. Experiments were conducted by varying the air pressure. At

25,000 Pa, the air flow improved. Increasing the pressure to 30,000, 35,000, and 40,000

Pa resulted in the cooled air flowing away from the blade, causing blockage and reduced

inlet air pressure. Reducing the pressure to 24,000 Pa caused the air to be retained,

preventing its exit through the holes and increasing blade temperature. The optimal

cooling was achieved at 25,000 Pa.

ATHEER RAHEEM ABDULLAH

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