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US 10,472,974 B2Granted
Turbomachine rotor blade
AssigneeGeneral Electric Company
InventorsMark Andrew Jones, James Tyson Balkcum, III
Life of this patent
Estimating the term…
Abstract
In one aspect, the present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining at least one cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a core fluidly coupled to the cooling passage. A maximum radial depth of the core is at least six times greater than a minimum hydraulic diameter of a largest cooling passage of the at least one cooling passage.
Claims16
A rotor blade for a turbomachine, the rotor blade comprising:
- an airfoil defining a leading edge, a trailing edge opposite the leading edge, and at least one cooling passage extending in a radial direction;
- and
- a tip shroud coupled to the airfoil, the tip shroud having a radially inner shroud surface;
- a core defined between the radially inner shroud surface of the tip shroud and the airfoil, the core comprising a core surface and a central plenum fluidly coupled to the at least one cooling passage;
- a first rib extending radially between the core surface and the radially inner shroud surface and axially between the leading edge and the trailing edge, the first rib defining therethrough a first plurality of cross-over apertures;
- wherein a maximum radial depth of the core is at least six times greater than a minimum hydraulic diameter of a largest cooling passage of the at least one cooling passage;
- and
- wherein the first rib comprises a first linear edge proximate the radially inner shroud surface and a first arcuate edge connected to each end of the first linear edge, the first arcuate edge being disposed in an axial direction, the first plurality of cross-over apertures including a first cross-over aperture and a second cross-over aperture, the remaining cross-over apertures of the first plurality of cross-over apertures being disposed in an arcuate, continuously concave pattern in the radial direction between the first cross-over aperture and the second cross-over aperture corresponding to a first arcuate shape of the first arcuate edge.
5 more elements
A rotor blade for a turbomachine, the rotor blade comprising:
- an airfoil having a leading edge and a trailing edge;
- a tip shroud coupled to the airfoil, the tip shroud and the airfoil at least partially defining a main body cavity and a central plenum therebetween;
- a first rib separating the main body cavity and the central plenum and extending radially between a core surface of the central plenum and a radially inner surface of the tip shroud, the first rib defining a first plurality of cross-over apertures fluidly coupling the central plenum and the main body cavity;
- wherein the first plurality of cross-over apertures includes a first cross-over aperture and a second cross-over aperture, the remaining cross-over apertures of the first plurality of cross-over apertures being disposed in an arcuate, continuously concave pattern in the radial direction between the first cross-over aperture and the second cross-over aperture.
1 more element
A rotor blade for a turbomachine, the rotor blade comprising:
- a root;
- an airfoil defining a span extending from the root of the airfoil to a tip shroud;
- the tip shroud coupled to the airfoil, the tip shroud including a side surface, the tip shroud and the airfoil at least partially defining a central plenum and a main body cavity;
- and
- a first rib extending radially from a core surface of the central plenum to a radially inner surface of the tip shroud, the first rib defining a plurality of cross-over apertures fluidly coupling the central plenum and the main body cavity, the plurality of cross-over apertures including a first cross-over aperture and a second cross-over aperture, the remaining cross-over apertures of the plurality of cross-over apertures disposed in an arcuate, continuously concave pattern in the radial direction between the first cross-over aperture and the second cross-over aperture,
- wherein the tip shroud and the airfoil collectively define a fillet, the fillet having a radius of curvature, a first end of the fillet intersecting the airfoil at a first runout point radially inward of ninety percent of the span as measured in a radial direction from the root.
3 more elements
Dependencies are inferred from the claim text.