Shroud honeycomb cutter
AssigneeUnited Technologies Corporation
InventorsBryan P. Dube, Richard Page
Life of this patent
Estimating the term…
Abstract
A turbine blade for use in a gas turbine engine is provided. The turbine blade includes an airfoil portion having a tip end, a shroud attached to the tip end, which shroud has an outer surface, and a knife edge attached to an outer surface of the shroud. The knife edge has a pair of cutter blades protruding outwardly from the knife edge.
Claims20
A turbine blade for use in a gas turbine engine, said turbine blade comprising:
- an airfoil portion having a tip end;
- a shroud attached to said tip end, said shroud having an outer surface;
- a knife edge attached to said outer surface of said shroud;
- and
- said knife edge having a pair of cutter blades protruding outwardly from said knife edge.
A shroud for a turbine blade, said shroud having an outer surface, a knife edge attached to said outer surface, and a plurality of cutter blades formed into said knife edge at a central location spaced from each end of said knife edge.
A method for manufacturing a turbine blade comprising:
- forming a turbine blade having an airfoil portion, a shroud attached to a tip end of said airfoil portion, and a knife edge attached to an outer surface of said shroud;
- and
- machining a pair of cutter blades into said knife edge so that said cutter blades are positioned substantially over said airfoil portion.
Dependencies are inferred from the claim text.