Adjusted rotating airfoil
AssigneesEdward Len Miller, Stephen Wayne Fiebiger, Reiner Jochen Digele, Wilm Philipp Hecker, Andreas Martin Mattheiss, Wes Carl Smith
InventorsEDWARD LEN MILLER, STEPHEN WAYNE FIEBIGER, WES Carl SMITH, Wilm Philipp Hecker, Andreas Martin Mattheiss, Reiner Jochen Digele
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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 blade, has an increased surface area over a portion of the airfoil chord length. The increased surface area allows for a greater amount of air to be taken in by the airfoil, thus increasing the air flow through the gas turbine engine.
Claims20
A compressor component having an attachment, a platform extending radially 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 X1 and Z1, for each distance Y1 in inches as set forth in Table 1, carried to three decimal places, wherein Y1 is a distance measured radially outward from an engine centerline, the X1 and Z1 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 blade, the airfoil having an uncoated profile substantially in accordance with Cartesian coordinate values of X1, Y1, and Z1 as set forth in Table 1, carried to three decimal places, wherein Y1 is a distance measured in inches, the X1 and Z1 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 disk having a plurality of compressor blades extending radially outward from the disk, each of the plurality of compressor blades having an airfoil with an uncoated nominal profile substantially in accordance with Cartesian coordinate values of 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 values with smooth continuing splines, and the airfoil sections are joined smoothly to form the airfoil profile, wherein the compressor blades are located adjacent to inlet guide vanes of the compressor, and the compressor blades have an axial length such that a stage of compressor vanes spaced directly downstream of the compressor blades have an axial length sized to compliment the profile of the compressor blades.
Dependencies are inferred from the claim text.