Adjusted stationary airfoil
AssigneesEdward Len Miller, Stephen Wayne Fiebiger, Andreas Martin Mattheiss, Reiner Jochen Digele, Wilm Philipp Hecker, Wes Carl Smith
InventorsEDWARD LEN MILLER, STEPHEN WAYNE FIEBIGER, WES Carl SMITH, Reiner Jochen Digele, Wilm Philipp Hecker, Andreas Martin Mattheiss
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Abstract
A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area.
Claims20
A compressor component having an attachment, a platform extending outward from the attachment and an airfoil extending radially outward from the platform, the airfoil having an uncoated profile substantially in accordance with Cartesian coordinate values of X and Z, for each distance Y in inches as set forth in Table 1, carried to three decimal places, wherein Y is a distance measured radially outward from an engine centerline, the X and Z coordinate values being joined in smooth continuing splines to form airfoil sections and the airfoil sections joined smoothly to form the profile.
An airfoil for a compressor vane, the airfoil having an uncoated profile substantially in accordance with Cartesian coordinate values X, Y, and Z as set forth in Table 1, carried to three decimal places, wherein Y is a distance measured in inches, the X and Z coordinate values being joined in smooth continuing splines to form airfoil sections and the airfoil sections joined smoothly to form the profile.
A compressor portion comprising a compressor casing having a plurality of compressor vanes extending radially from the disk, each of the plurality of compressor vanes having an airfoil with an uncoated nominal profile substantially in accordance with Cartesian coordinate values X, Y, and Z, set forth in inches in Table 1, with the Y coordinate values at perpendicular distances from planes normal to a radius from an engine centerline, wherein airfoil sections are defined at each distance Y by connecting the X and Z coordinate value with smooth continuing splines, and the airfoil sections are joined smoothly to form the airfoil profile,
- wherein the compressor vanes are located adjacent to a set of rotating compressor blades having an increased chord length, such that the compressor vanes have a corresponding decreased chord length to compliment the compressor blades.
Dependencies are inferred from the claim text.