Triangular serpentine cooling channels
First Claim
1. A cooled airfoil comprising:
- a concave pressure wall extending radially from a base to a tip of the airfoil;
a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge; and
a plurality of cooling channels extending radially between the base and the tip of the airfoil between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply through the base of the airfoil, the cooling channels comprising;
a leading edge channel;
a trailing edge channel;
a serpentine cooling circuit comprising;
a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with a supply channel through the base of the airfoil;
a down-pass channel forward of and in flow communication with the first up-pass channel; and
a second up-pass channel forward of and in flow communication with the down-pass channel;
wherein at least the down-pass channel and the second up-pass channel comprise a generally triangular transverse cross-sectional shape;
a dedicated up-pass channel arranged between the leading edge channel and the second up-pass channel of the serpentine cooling circuit; and
an axial channel that is arranged adjacent the tip and in flow communication with and extending aftward from one of the second up-pass channel of the serpentine cooling circuit, the dedicated up-pass channel, or the trailing edge channel toward the trailing edge.
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Accused Products
Abstract
A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and cooling channels extending radially between the base and the tip of the airfoil between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply through the base of the airfoil. The cooling channels include a leading edge channel, a trailing edge channel, a serpentine cooling circuit, and a dedicated up-pass channel. The serpentine cooling circuit includes a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with a supply channel through the base of the airfoil, a down-pass channel forward of and in flow communication with the first up-pass channel, and a second up-pass channel forward of and in flow communication with the down-pass channel. At least the down-pass channel and the second up-pass channel of the serpentine circuit have a generally triangular transverse cross-sectional shape. The dedicated up-pass channel is arranged between the leading edge channel and the second up-pass channel of the serpentine cooling circuit.
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Citations
23 Claims
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1. A cooled airfoil comprising:
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a concave pressure wall extending radially from a base to a tip of the airfoil; a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge; and a plurality of cooling channels extending radially between the base and the tip of the airfoil between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply through the base of the airfoil, the cooling channels comprising; a leading edge channel; a trailing edge channel; a serpentine cooling circuit comprising; a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with a supply channel through the base of the airfoil; a down-pass channel forward of and in flow communication with the first up-pass channel; and a second up-pass channel forward of and in flow communication with the down-pass channel; wherein at least the down-pass channel and the second up-pass channel comprise a generally triangular transverse cross-sectional shape; a dedicated up-pass channel arranged between the leading edge channel and the second up-pass channel of the serpentine cooling circuit; and an axial channel that is arranged adjacent the tip and in flow communication with and extending aftward from one of the second up-pass channel of the serpentine cooling circuit, the dedicated up-pass channel, or the trailing edge channel toward the trailing edge. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A gas turbine blade comprising:
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a root including a plurality of radially extending supply channels; a concave pressure wall extending radially from the root to a tip of the blade; a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge; a plurality of cooling channels extending radially between the base and the tip of the blade between the concave pressure wall and the convex suction wall and configured to receive cooling fluid from the supply channels in the root, the cooling channels comprising; a leading edge channel; a trailing edge channel; a serpentine cooling circuit comprising; a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with one of the supply channels in the root; a down-pass channel forward of and in flow communication with the first up-pass channel; and a second up-pass channel forward of and in flow communication with the down-pass channel; wherein at least the down-pass channel and the second up-pass channel comprise a generally triangular transverse cross-sectional shape; a dedicated up-pass channel arranged between the leading edge channel and the second up-pass channel of the serpentine cooling circuit; and an axial channel that is arranged adjacent the tip and in flow communication with and extending aftward from one of the second up-pass channel of the serpentine cooling circuit, the dedicated up-pass channel, or the trailing edge channel toward the trailing edge. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19)
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20. A gas turbine engine comprising:
one or more rotors each of which rotors comprise a plurality of rotor blades circumferentially arranged about a rotation axis of the engine, wherein one or more of the rotor blades comprise; a root including a plurality of radially extending supply channels; a concave pressure wall extending radially from the root to a tip of the blade; a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge; a plurality of cooling channels extending radially between the base and the tip of the blade between the concave pressure wall and the convex suction wall and configured to receive cooling fluid from the supply channels in the root, the cooling channels comprising; a leading edge channel; a trailing edge channel; a serpentine cooling circuit comprising; a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with one of the supply channels in the root; a down-pass channel forward of and in flow communication with the first up-pass channel; and a second up-pass channel forward of and in flow communication with the down-pass channel; wherein at least the down-pass channel and the second up-pass channel comprise a generally triangular transverse cross-sectional shape; a dedicated up-pass channel arranged between the leading edge channel and the second up-pass channel of the serpentine cooling circuit; and an axial channel that is arranged adjacent the tip and in flow communication with and extending aftward from one of the second up-pass channel of the serpentine cooling circuit, the dedicated up-pass channel, or the trailing edge channel toward the trailing edge. - View Dependent Claims (21, 22, 23)
Specification