Patent ID: 9011087
Filing Date: 2015-04-21
Classification: F01D,F05D

Abstract:
1. A hybrid airfoil for a gas turbine engine, comprising: a leading edge portion; a trailing edge portion; an intermediate portion between said leading edge portion and said trailing edge portion, wherein said intermediate portion is a solid section of the hybrid airfoil that excludes any radial passages, and wherein said leading edge portion is made of a first material, said trailing edge portion is made of a second material, and said intermediate portion is made of a third material, and at least two of said first material, said second material and said third material are different materials; a rib disposed between said leading edge portion and said intermediate portion, wherein a protrusion of one of said rib and said intermediate portion is received within a pocket of the other of said rib and said intermediate portion; and an intermediate bonding layer between said rib and said intermediate portion.