Turbine airfoil cooling passageway
AssigneeUnited Technologies Corporation
InventorsEdward Pietraszkiewicz, John Calderbank, Andrew Milliken, Jeffrey Levine
Life of this patent
Estimating the term…
Abstract
An internally cooled gas turbine engine turbine vane has an outboard shroud and an airfoil extending from an outboard end at the shroud to an inboard end. A cooling passageway has an inlet in the shroud, a first turn at least partially within the airfoil, a first leg extending from the inlet inboard through the airfoil to the first turn, and a second leg extending from the first turn. A dividing wall is in the passageway and has an upstream end in an outboard half of a span of the airfoil and has a plurality of vents. The vane may be formed as a reengineering of a baseline configuration lacking the dividing wall.
Claims20
An internally-cooled gas turbine engine turbine vane comprising:
- an outboard shroud;
- an airfoil extending from an outboard end at the shroud to an inboard end;
- a cooling passageway having:
- an inlet in the shroud;
- a first turn at least partially within the airfoil;
- a first leg extending from the inlet inboard through the airfoil to the first turn;
- and
- a second leg extending from the first turn;
- and
- a dividing wall in the passageway and having:
- an upstream end in an outboard half of a span of the airfoil;
- a plurality of vents.
An internally-cooled turbomachine element comprising:
- an airfoil extending between inboard and outboard ends;
- and
- internal surface portions defining a cooling passageway at least partially within the airfoil, wherein:
- the cooling passageway has a first turn from an upstream first leg to a downstream second leg;
- a dividing wall bifurcates a section of the cooling passageway into first and second portions and extends within the passageway along a length from a wall first end in the first leg to a wall second end, the wall first end being in an upstream half of a portion of the first leg within the airfoil, there being no additional features extending between airfoil pressure and suction side walls along the first leg;
- and
- the dividing wall has a plurality of apertures.
A method for reengineering a configuration for an internally-cooled turbomachine element from a baseline configuration to a reengineered configuration wherein the baseline configuration has an internal passageway through an airfoil and having first and second generally spanwise legs and a first turn therebetween, the method comprising:
- adding a wall to bifurcate the passageway into first and second portions, the wall extending within the passageway along a length from a wall first end to a wall second end;
- and
- otherwise essentially maintaining a basic shape of the first cooling passageway.
Dependencies are inferred from the claim text.