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US 2010/0135812 A1Published application
Turbine blade apparatus
AssigneeGeneral Electric Company
InventorsRonald Ralph Cairo, Arthur Samuel Peck
Life of this patent
Estimating the term…
Abstract
A gas turbine airfoil is disclosed. The gas turbine airfoil includes a root section, a separate extension section attached to the root section, and a joint disposed between the root section and the extension section, the joint including at least one of a mechanical interlock and a metallurgical bond.
Claims21
A gas turbine airfoil comprising:
- a root section;
- a separate extension section attached to the root section;
- and
- a joint disposed between the root section and the extension section and disconnected from an aerodynamic surface of the gas turbine airfoil, the joint including at least one of a mechanical interlock and a metallurgical bond.
1 more element
A method of assembling a gas turbine airfoil comprising:
- applying a bonding agent to at least one of a protrusion and a recess, one each of the protrusion and the recess opposingly disposed on one each of a root section of the airfoil and a separate extension section of the airfoil;
- positioning the root section relative to the extension section;
- exposing the protrusion, the recess, and the bonding agent to a species capable of activating the bonding agent;
- and
- creating a metallurgical bond between the root section and the extension section.
2 more elements
A gas turbine, comprising:
- a casing to direct a gas flow;
- a rotor;
- and
- a plurality of gas turbine airfoils, at least one of the plurality of gas turbine airfoils comprising:
- a root section in mechanical connection with the rotor;
- and
- a separate extension section attached to the root section via a joint disposed between the root section and the extension section and disconnected from an aerodynamic surface of the gas turbine airfoil.
4 more elements
Dependencies are inferred from the claim text.