Patent ID: 7334997

Claim:
An integral rotor assembly for a gas turbine engine, comprising: a metallic hub having an annular flowpath surface; and at least one blade extending outwardly from said flowpath surface, said blade comprising: a metallic body having a first density, said body being integral with said hub and defining a shank portion and an airfoil portion having opposed pressure and suction sides; a non-metallic insert having a second density less than said first density, said insert carried by a pocket formed in the airfoil portion of said body, wherein said insert and said body collectively define an airfoil shape having a leading edge and an opposed trailing edge; a non-metallic outer skin disposed about the airfoil portion of said body; and an erosion coating disposed about at least a portion of said outer skin, said erosion coating having a metallic portion adjacent the leading edge and a non-metallic portion extending along the pressure side and the suction side from the metallic portion to the trailing edge; and at least one cavity formed within the shank portion of said body and extending towards the airfoil portion.