Abstract: High-pressure turbine blade (HPTB) shrouds suffer manufacturing variations in both platform alignment and inter-platform gap width. Compared to hub endwalls, the aerothermal effects of shroud platform steps and gaps has ...

Abstract: In this paper, we consider the impact of trailing edge burn-back on the aerodynamic performance of cooled transonic high-pressure nozzle guide vanes. We consider four levels of burn-back ranging from new parts to severely ...

Abstract: An experimental and numerical study was conducted on fan-shaped holes on the pressure surface of a high-pressure turbine blade. Blockages in these film holes can arise through dirt accumulation as well as erosion of the ...

Abstract: In this paper we experimentally evaluate the impact of in-service deterioration on the aerodynamic performance of heavily film-cooled high-pressure nozzle guide vanes from large civil jet engines. We study 15 mid-life to ...