Hybrid blisk
AssigneeGeneral Electric Company
InventorApostolos Karafillis
Life of this patent
Estimating the term…
Abstract
A rotor assembly or “blisk” for a gas turbine engine includes a metallic hub having an annular flowpath surface, and at least one blade extending outwardly from the flowpath surface. The blade includes a metallic body having a first density. The metallic body defines a shank portion and an airfoil portion having opposed pressure and suction sides, and is integral with the hub. An insert having a second density less than the first density is carried by the body, and the insert and the body collectively define an airfoil shape. A method is also provided for manufacturing a rotor assembly.
Claims17
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.
A method of making an integral rotor assembly for a gas turbine engine, comprising:
- forming a metallic hub having an annular flowpath surface;
- and
- forming at least one blade integral to said hub and 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.
Dependencies are inferred from the claim text.