TURBINE BLADE WITH NEAR WALL MICROCIRCUIT EDGE COOLING

摘要

Micro-circuit cooling channels that provide thin wall leading edge and trailing edge cooling for a turbine blade. The blade includes an outer housing wall defining an enclosure and a plurality of ribs extending at least a portion of the length of the blade within the enclosure and defining a serpentine flow channel that allows a cooling airflow to flow from a proximal end to a distal end of the enclosure. The micro-circuit cooling channels are positioned at the leading edge of the airfoil and the trailing edge of the airfoil and include a plurality of micro-pins extending across the micro-circuit cooling channel.

主权项

1. A blade for a gas turbine engine, said blade comprising:
an airfoil including an outer housing wall defining an enclosure, a leading edge and a trailing edge; a plurality of ribs extending at least a portion of the length of the airfoil within the enclosure and defining a serpentine flow channel that allows a cooling airflow to flow from a proximal end to a distal end of the airfoil; and a leading edge micro-circuit cooling channel positioned at the leading edge of the airfoil and including a plurality of micro-pins extending across the micro-circuit cooling channel, wherein the leading edge micro-circuit cooling channel is positioned within a wall of the enclosure to be within 0.005-0.008 inches of an outer surface of the leading edge of the airfoil.