Effect of Stator Leading and Trailing Edge Coolant Flow on Performance of Typical High Pressure Turbine Stage of a Gas Turbine Engine

Effect of Stator Leading and Trailing Edge Coolant Flow on Performance of Typical High Pressure Turbine Stage of a Gas  Turbine Engine:

The Nozzle Guide Vane (NGV) of High Pressure (HP) turbine of modern military gas turbine is extensively cooled to reap the benefits of using higher cycle temperatures and to ensure longer life of the turbine components. NGV of the HP turbine encounters the maximum temperature from the combustion chamber. Hence, cooling of the NGV is essential from creep and thermal fatigue points of view. Compressor Bleed air is used for cooling the NGV and due to addition of mass, leads to decrease in turbine efficiency and increase in losses. The objective of the present study is to determine numerically using 3D Navier Stokes (NS) solver, the effect of Leading edge (LE) and Trailing Edge (TE) coolant ejection on the performance of the NGV via blade loading, efficiency and exit flow angles for different mass ratios