Cooling passageway turn
AssigneeUnited Technologies Corporation
InventorsWilliam S. Kvasnak, Kenneth K. Landis, Hans R. Przirembel
Life of this patent
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Abstract
An internally-cooled turbomachine element has an airfoil extending between inboard and outboard ends. A cooling passageway is at least partially within the airfoil and has at least a first turn. Means are in the passageway for limiting a turning a loss of the first turn. The turbomachine element may result from a reengineering of an existing element configuration lacking such means.
Claims30
An internally-cooled turbomachine element comprising:
- an airfoil extending between inboard and outboard ends;
- a cooling passageway at least partially within the airfoil and having at least a first turn;
- and
- means in the passageway for limiting a turning loss of the first turn and comprising a wall essentially dividing the entirety of the first turn into first and second flowpath portions, a leading end of the wall being 1.0–3.0 hydraulic diameters upstream of the first turn.
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 a first leg to a second leg;
- a dividing wall bifurcates the cooling passageway into first and second portions and extends within the passageway along a length from a wall first end to a wall second end;
- and
- the wall first end is 1.0–3.0 hydraulic diameters from an end of the first leg at the first turn.
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 having first and second 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.
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 a first leg to a second leg;
- a dividing wall bifurcates the cooling passageway into first and second portions and extends within the passageway along a length from a wall first end to a wall second end;
- the passageway has a second turn from the second leg to a third leg;
- the wall first end is 1.0–3.0 hydraulic diameters from an end of the first leg at the first turn;
- and
- the wall second end is 1.0–3.0 hydraulic diameters from an end of the third leg at the second turn.
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 a first leg to a second leg;
- a dividing wall bifurcates the cooling passageway into first and second portions and extends within the passageway along a length from a wall first end to a wall second end;
- the passageway has a second turn from the second leg to a third leg;
- at the first turn, the passageway first portion is within the second portion;
- and
- at the second turn, the passageway second portion is within the first portion.
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 a first leg to a second leg;
- a dividing wall bifurcates the cooling passageway into first and second portions and extends within the passageway along a length from a wall first end to a wall second end;
- the wall has a plurality of apertures therein;
- and
- the plurality of apertures are no closer than two hydraulic diameters from the first turn.
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 a first leg to a second leg;
- a dividing wall bifurcates the cooling passageway into first and second portions and extends within the passageway along a length from a wall first end to a wall second end;
- the passageway has a second turn from the second leg to a third leg;
- the wall first end is proximate an end of the first leg at the first turn;
- and
- the wall second end is proximate an end of the third leg at the second turn.
Dependencies are inferred from the claim text.