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US 2016/0258296 A1Published application
Airfoil for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsRussell J. Bergman, Jess J. Parkin
Life of this patent
Estimating the term…
Abstract
A component for a gas turbine engine includes an airfoil that has a first end. A first platform is located at the first end of the airfoil. A compound fillet includes a first fillet portion tangent to the first platform and an airfoil offset. A second fillet portion is tangent to a surface of the airfoil and the first fillet portion.
Claims20
A component for a gas turbine engine comprising:
- an airfoil having a first end;
- a first platform located at the first end of the airfoil;
- and
- a compound fillet including a first fillet portion tangent to the first platform and an airfoil offset and a second fillet portion tangent to a surface of the airfoil and the first fillet portion.
1 more element
A gas turbine engine comprising:
- an airfoil located in one of a compressor section or a turbine section;
- a first platform attached to the airfoil;
- a compound fillet including a first fillet portion tangent to the first platform and an airfoil offset and a second fillet portion tangent to a surface of the airfoil and the first fillet portion.
A method of forming an airfoil comprising:
- locating a platform relative to an airfoil;
- forming a first fillet portion tangent to the platform and an airfoil offset;
- and
- forming a second fillet portion tangent to the first fillet portion and a surface of the airfoil.
1 more element
Dependencies are inferred from the claim text.