Aerothermal Analysis of Suction Side Film Cooling in a High-Pressure Nozzle Guide Vane Cascade

A specific designed film-cooled nozzle guide vane cascade was tested in a high speed facility to determine the influence of suction side film cooling on the profile loss. Wake traverses with a five-hole probe and measurements of profile pressure distribution were conducted under Ma2th = 0:8 and Re2th ≈ 106 with coolant ejection from two different rows of cooling holes located upstream of the passage throat on the suction surface. In order to clarify the differences in loss behaviour noticed between the investigated film cooling rows, numerical simulations of the experiments were carried out, allowing an in-depth comprehension of the flow phenomena taking place in the mixing layer downstream of the coolant injection point. Additional simulations of the film cooling effectiveness were conducted for both investigated rows.