Patent ID: 7575414
Filing Date: 2009-08-18
Classification: F01D,F05D,Y02T

Abstract:
1. An airfoil for a gas turbine engine, said airfoil having a longitudinal axis, a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls, and comprising: an array of radially-spaced apart, longitudinally-extending partitions defining a plurality of cooling channels therebetween; a plurality of aft pins disposed in at least one of said cooling channels and extending between said pressure and suction sidewalls; a plurality of elongated turbulators disposed in at least one of said cooling channels said turbulators oriented at an angle to said longitudinal axis such that an aft end of each of said turbulators is closer to an adiacent partition than a forward end of said turbulator; and an array of radially-spaced apart, longitudinally-extending dividers defining a plurality of trailing edge slots therebetween, each of said trailing edge slots having an inlet in fluid communication with said trailing edge cavity and an axially-downstream exit; wherein an exposed first land extends downstream from each of alternate ones of said dividers to said trailing edge and each of said lands includes: spaced-apart longitudinally extending side faces which intersect said suction sidewall and a concave fillet extending between each of said side faces and said suction sidewall; and wherein each of said fillets has: immediately adjacent said trailing edge slot exits, a first radius, downstream of said trailing edge slot exits, a second radius greater than said first radius; and adjacent said trailing edge, a third radius greater than said first radius and less than said second radius.