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US 8,998,571 B2Granted
Slotted turbine airfoil
AssigneeGeneral Electric Company
InventorsSteven Sebastian Burdgick, Alberto Di Sante
Life of this patent
Estimating the term…
Abstract
A slotted turbine static nozzle airfoil. In one embodiment, the turbine static nozzle airfoil includes a concave pressure wall having a slot extending therethrough; a convex suction wall adjoined with the concave pressure wall at respective end joints; and a pocket fluidly connected with the slot and located between the convex suction wall and the concave pressure wall, wherein at least one of the convex suction wall or the concave pressure wall includes a thinned segment proximate one of the respective end joints, the thinned segment configured to extend the pocket toward a trailing edge of the turbine static nozzle airfoil.
Claims13
A turbine static nozzle airfoil comprising:
- a concave pressure wall having a slot extending there through;
- a convex suction wall adjoined with the concave pressure wall at respective end joints;
- and
- a pocket fluidly connected with the slot and located between the convex suction wall and the concave pressure wall,
- wherein at least one of the convex suction wall or the concave pressure wall includes a thinned segment proximate one of the respective end joints, the thinned segment configured to extend the pocket toward a trailing edge of the turbine static nozzle airfoil,
- wherein the respective end joints include weld joints, and wherein a first one of the weld joints is located proximate a leading edge of the turbine static nozzle airfoil, and wherein a second one of the weld joints is located at the trailing edge of the turbine static nozzle airfoil,
- wherein the slot is located within the thinned segment that is proximate the trailing edge of the airfoil and abutting the second one of the weld joints, and
- wherein the slot extends entirely through the thinned segment only on the concave pressure wall.
5 more elements
A turbine stator comprising:
- axially dispersed sets of nozzles for directing a working fluid,
- wherein one of the axially dispersed sets of nozzles includes a plurality of turbine static nozzle airfoils, each of the turbine static nozzle airfoils having:
- a concave pressure wall having a slot extending therethrough;
- a convex suction wall adjoined with the concave pressure wall at respective end joints;
- and
- a pocket fluidly connected with the slot and located between the convex suction wall and the concave pressure wall,
- wherein at least one of the convex suction wall or the concave pressure wall includes a thinned segment proximate one of the respective end joints, the thinned segment extending the pocket toward a trailing edge of the turbine static nozzle airfoil,
- wherein the respective end joints include weld joints, and wherein a first one of the weld joints is located proximate a leading edge of the turbine static nozzle airfoil, and wherein a second one of the weld joints is located at the trailing edge of the turbine static nozzle airfoil,
- wherein the slot is located within the thinned segment that is proximate the trailing edge of the airfoil and abutting the second one of the weld joints, and
- wherein the slot extends entirely through the thinned segment only on the concave pressure wall.
7 more elements
A turbine static nozzle comprising:
- a pair of endwalls;
- and
- a nozzle airfoil dispersed between and connected with each of the pair of endwalls, the nozzle airfoil including:
- a concave pressure wall having a slot extending therethrough;
- a convex suction wall adjoined with the concave pressure wall at respective end joints;
- and
- a pocket fluidly connected with the slot and located between the convex suction wall and the concave pressure wall,
- wherein at least one of the convex suction wall or the concave pressure wall includes a thinned segment proximate one of the respective end joints, the thinned segment extending the pocket toward a trailing edge of the turbine static nozzle airfoil,
- wherein the respective end joints include weld joints, and wherein a first one of the weld joints is located proximate a leading edge of the turbine static nozzle airfoil, and wherein a second one of the weld joints is located at the trailing edge of the turbine static nozzle airfoil,
- wherein the slot is located within the thinned segment that is proximate the trailing edge of the airfoil and abutting the second one of the weld joints, and
- wherein the slot extends entirely through the thinned segment only on the concave pressure wall.
8 more elements
Dependencies are inferred from the claim text.