Patent ID: 9039382
Filing Date: 2015-05-26
Classification: F01D,F05D,Y02T

Abstract:
1. A gas turbine engine blade comprising: a proximal end and a radially opposite distal end, and a forward side and an axially opposite aft side; an airfoil, a platform, a shank, and a dovetail; wherein said airfoil extends distally from said platform and terminates at said distal end, said shank extends proximally from said platform, and said dovetail extends proximally from said shank and terminates at said proximal end; a skirt disposed at least partially on an aft side of said shank and extending at least partially from said shank in a direction that is at least partially axially aft of said shank; wherein said skirt includes a skirt radius which serves as a transitioning surface between a proximal surface of said skirt and an aft surface of said shank and also between said aft surface of said shank and a lateral side of said shank.