10th European Conference on Turbomachinery Fluid dynamics & Thermodynamics
Heat Transfer & Cooling
The present study concentrates on a cooled trailing edge in a linear cascade of highpressure turbine nozzle guide vanes. The pressure side cooling features two rows of cooling holes followed by a trailing edge cutback with film cooling slots, stiffened by evenly spaced ribs in an inline configuration. The present study evaluates the reliability of steady RANS predictions in such a complex cooling system. Coolant-to-mainstream mass flow ratio values in the range of 1% to 2.8% were simulated at exit Mach number of M2is = 0.2. The computed performance of the trailing edge cooling scheme was compared to aerodynamic and thermal measurements, with the aim of understanding the coolant-mainstream interaction at the cutback slot exit. Despite the well-known limitations of the steady framework in simulating film cooling effectiveness, the modeling provided reasonable predictions of the discharge behavior of both cutback slot and cooling holes.