Snubber configurations for turbine rotor blades
AssigneeGeneral Electric Company
InventorsJoseph Anthony Weber, Mark Andrew Jones
Life of this patent
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Abstract
A rotor blade for use in a turbine of a combustion turbine engine. The rotor blade may include an airfoil having a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the root and an outboard tip. The rotor blade may further include dual snubber shrouds positioned on the airfoil. Each of the dual snubber shrouds may be configured to engage a corresponding snubber shroud on at least one neighboring rotor blade upon installation.
Claims20
A rotor blade for use in a turbine of a combustion turbine engine, the rotor blade comprising an airfoil that extends from a connection with a root, the airfoil including a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the root and an outboard tip, the rotor blade further comprising:
- dual snubber shrouds positioned on the airfoil;
- wherein each of the dual snubber shrouds is configured to engage a corresponding dual snubber shroud on at least one neighboring rotor blade upon installation.
A gas turbine engine having a turbine that comprises a row of circumferentially spaced rotor blades, wherein each of the rotor blades includes an airfoil extending from a root that connects to a rotor disc, the airfoil including a pressure sidewall and a suction sidewall extending axially between a leading edge and a trailing edges and radially between a platform that forms an outboard boundary of the root and an outboard tip of the airfoil, the airfoil of each of the rotor blades further comprising:
- dual snubber shrouds, an inboard snubber shroud and an outboard snubber shroud;
- wherein each of the snubber shrouds comprises a position between the platform and the outboard tip of the airfoil and a configuration that connects each of the rotor blades to neighboring rotor blades positioned to each side;
- and
- wherein the outboard snubber shroud comprises a shroud positioned near the outboard tip of the airfoil and the inboard snubber shroud comprises a shroud positioned near a radial mid-region of the airfoil.
Dependencies are inferred from the claim text.