TRAILING EDGE AND TIP COOLING
First Claim
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1. A gas turbine engine component comprising:
- an airfoil extending radially from a root section to a tip section and comprising a trailing edge cooling passageway;
a plurality of first flow dividers in the cooling passageway, the first flow dividers having a first longitudinal axis;
at least one second flow divider in the cooling passageway between the plurality of first flow dividers and the tip section, the at least one second flow divider having a second longitudinal axis that is offset by a first angle with respect to the first longitudinal axis;
a third flow divider in the cooling passageway between the at least one second flow divider and the tip section, the third flow divider having a third longitudinal axis that is offset by a second angle with respect to the first longitudinal axis, wherein the second angle is different from the first angle.
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Abstract
A gas turbine engine component includes an airfoil extending radially from a root section to a tip section and having a trailing edge cooling passageway and first, second and third flow dividers in the cooling passageway. The first, second and third flow dividers have longitudinal axes that are angled based upon a position of the flow divider relative to the tip section of the airfoil.
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Citations
23 Claims
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1. A gas turbine engine component comprising:
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an airfoil extending radially from a root section to a tip section and comprising a trailing edge cooling passageway; a plurality of first flow dividers in the cooling passageway, the first flow dividers having a first longitudinal axis; at least one second flow divider in the cooling passageway between the plurality of first flow dividers and the tip section, the at least one second flow divider having a second longitudinal axis that is offset by a first angle with respect to the first longitudinal axis; a third flow divider in the cooling passageway between the at least one second flow divider and the tip section, the third flow divider having a third longitudinal axis that is offset by a second angle with respect to the first longitudinal axis, wherein the second angle is different from the first angle. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. A component for a gas turbine engine comprising:
an airfoil extending radially from an inner diameter to an outer diameter and axially from a leading edge to a trailing edge, the airfoil comprising; an internal chamber; a plurality of radially spaced cooling slots in communication with the internal chamber, the cooling slots terminating at outlets at the trailing edge; and a radial column of flow dividers extending between adjacent cooling slots, the column of flow dividers comprising; a tip flow divider spaced from the outer diameter by a first cooling air slot; an intermediate flow divider spaced from the tip flow divider by a second cooling air slot; and a first oblong pedestal spaced from the intermediate flow divider by a third cooling air slot, wherein the intermediate flow divider is oriented at a first angle relative to the oblong pedestal, and wherein the tip flow divider is oriented at a second angle relative to the first oblong pedestal, and wherein the first angle is different from the second angle. - View Dependent Claims (14, 15, 16, 17, 18, 19, 20, 21, 22)
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23. An airfoil aligned with an axis of rotation, the airfoil comprising:
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a leading edge extending along an upstream portion of the airfoil; a trailing edge located axially downstream from the leading edge; first and second inner surfaces defining a cooling passageway that extends upstream from the trailing edge; and a plurality of flow dividers, each flow divider extending from the first inner surface to the second inner surface and having a longitudinal axis, wherein the longitudinal axis of a given flow divider is angled relative to the axis of rotation based on a position of the flow divider relative to the outer diameter of the airfoil.
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Specification