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US 8,282,354 B2Granted
Reduced weight blade for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorBrandon W. Spangler
Life of this patent
Estimating the term…
Abstract
A rotor blade for a gas turbine engine having an edge buttress having an aperture. A method of reducing rotor blade weight includes removing material from within a truss area bounded by a platform section, an internal airfoil cooling passage, and an underplatform fillet.
Claims19
A rotor blade for a turbine engine comprising:
- an edge buttress having an aperture, said aperture extends at least partially through said edge buttress and an aperture platform cooling aperture in communication with said aperture.
A rotor blade for a turbine engine comprising:
- a platform section;
- an airfoil section which extends from said platform section;
- a neck section which extends from said platform section opposite said airfoil section, said neck section and said airfoil section contains an internal airfoil cooling passage;
- and
- an underplatform fillet adjacent said neck section and said platform section, said platform section, said internal airfoil cooling passage, and said underplatform fillet defines a truss shape which bounds an aperture wherein said truss shape is generally triangular in shape.
2 more elements
A method of reducing rotor blade weight comprising:
- removing material from within a truss area bounded by a platform section, an internal airfoil cooling passage, and an underplatform fillet of a rotor blade and
- removing material to define an aperture which extends completely through a neck section of the rotor blade.
A rotor blade for a turbine engine comprising:
- a platform section;
- an airfoil section which extends from said platform section;
- a neck section which extends from said platform section opposite said airfoil section, said neck section and said airfoil section contains an internal airfoil cooling passage;
- and
- an underplatform fillet adjacent said neck section and said platform section, said platform section, said internal airfoil cooling passage, and said underplatform fillet defines a truss shape which bounds an aperture wherein said aperture extends completely through said neck section.
2 more elements
Dependencies are inferred from the claim text.