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US 11,377,972 B1Granted
Airfoil profile
AssigneeDoosan Heavy Industries Construction Co., Ltd
InventorsJaehoon Chung, Krishna C. Veluru, Sungryong Lee, Jaewook Song
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Abstract
Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.
Claims20
A compressor component comprising:
- a root portion;
- and
- an airfoil portion extending from the root portion, the airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
- wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system,
- wherein a point of origin of the orthogonally related X, Y, and Z axes is located on an engine centerline,
- wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections, and
- wherein the plurality of airfoil profile sections, when joined together by smooth continuous arcs, form an airfoil shape.
4 more elements
A compressor vane, comprising:
- an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
- wherein the X, Y, and Z coordinate values are distances in inches measured in a Cartesian coordinate system,
- wherein a point of origin of the orthogonally related X, Y, and Z axes is located on an engine centerline,
- wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections, and
- wherein the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.
2 more elements
A compressor, comprising:
- a casing;
- and
- a plurality of compressor vanes coupled to the casing, the plurality of compressor vanes circumferentially spaced around the casing and extending towards a center axis of the compressor, wherein each compressor vane of the plurality of compressor vanes has an airfoil comprising:
- an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
- wherein the X, Y, and Z coordinate values are distances in inches measured in a Cartesian coordinate system,
- wherein a point of origin of the orthogonally related X, Y, and Z axes is located on an engine centerline,
- wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections, and
- wherein the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.
5 more elements
Dependencies are inferred from the claim text.