Patent ID: 9091175
Filing Date: 2015-07-28
Classification: F01D,Y10T

Abstract:
1. A gas turbine engine blade comprising an airfoil extending from a platform to a tip between a leading edge and a trailing edge, said airfoil having a hollow core portion adjacent said leading edge and spaced-apart from said trailing edge in a chordwise direction, the hollow core portion extending from the platform to the tip, and a stiffener rib provided in the hollow core portion of said airfoil and extending across a thickness of the airfoil between opposed side walls of the hollow core portion, the stiffener rib being positioned closer to the leading edge than the trailing edge in the chordwise direction, the stiffener rib having an elongated cross-section including a longitudinal length L greater than a width W, the stiffener rib having a longitudinal axis which is angled to have a radial upward component and an axial component in a direction away from the leading edge of the airfoil, the longitudinal axis of the stiffener rib extending through the trailing edge at a location adjacent to a trailing edge tip corner where the trailing edge meets the tip of the blade.