Abstract: Replacing natural gas fuels with coalderived syngas in industrial gas turbines can lead to molten particle deposition on the turbine components. The deposition of the particles, which originate from impurities in the syngas ...

Abstract: A common design for cooling the combustor liner of gas turbines is a double wall composed of impingement jets that feed effusion cooling holes. An important cooling mechanism associated with the effusion hole is the ...

Abstract: Endwall contouring is a technique used to reduce the strength and development of threedimensional secondary flows in a turbine vane or blade passage in a gas turbine. The secondary flows locally affect the external heat ...

Abstract: Everincreasing thermal loads on gas turbine components require improved cooling schemes to extend component life. Engine designers often rely on multiple thermal protection techniques, including internal cooling and external ...

Abstract: Shaped film cooling holes have become a standard geometry for protecting gas turbine components. Few studies, however, have reported flowfield measurements for moderately expanded shaped holes and even fewer have reported ...

Abstract: While much is known about how macrogeometry of shaped holes affects their ability to successfully cool gas turbine components, little is known about the influence of surface roughness on cooling hole interior walls. For ...

Abstract: The boundary layer on the endwall of an axial turbomachine passage is influenced by streamwise and crossstream pressure gradients, as well as a large streamwise vortex, that develop in the passage. These influences distort ...

Abstract: Shaped holes are increasingly selected for airfoil cooling in gas turbines due to their superior performance over that of cylindrical holes, especially at high blowing ratios. The performance of shaped holes is regarded ...

Abstract: The combustorturbine interface is an essential component in a gas turbine engine as it allows for thermal expansion between the first stage turbine vanes and combustor section. Although not considered as part of the external ...

Abstract: Turbine blade components in an engine are typically designed with gaps between parts due to manufacturing, assembly, and operational considerations. Coolant is provided to these gaps to limit the ingestion of hot combustion ...