Airfoil profile with optimized aerodynamic shape
First Claim
1. An aerodynamic profile for an airfoil, comprising:
- an uncoated, nominal shape formed by fairing a plurality of radial sections, said sections located within an envelope of ±
0.006 inches in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches as listed in Table 1; and
wherein R is a perpendicular distance from a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction and the X and Y values are perpendicular distances from the airfoil stacking line.
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Accused Products
Abstract
Provided is an aerodynamic profile for use in gas turbine airfoil and a turbine blade comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.
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Citations
8 Claims
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1. An aerodynamic profile for an airfoil, comprising:
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an uncoated, nominal shape formed by fairing a plurality of radial sections, said sections located within an envelope of ±
0.006 inches in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches as listed in Table 1; andwherein R is a perpendicular distance from a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction and the X and Y values are perpendicular distances from the airfoil stacking line. - View Dependent Claims (2)
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3. A gas turbine blade comprising:
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an airfoil profile, said profile having a nominal and uncoated shape formed by fairing a plurality of radial sections, said sections located within an envelope of ±
0.006 inches in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches as listed in Table 1; andwherein R is a perpendicular distance from a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction and the X and Y values are perpendicular distances from the airfoil stacking line. - View Dependent Claims (4)
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5. An aerodynamic profile for an airfoil, comprising:
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a nominal and uncoated shape formed by fairing a plurality of radial sections, said sections located within an envelope of ±
0.006 inches in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches as listed in Table 1, wherein R is a perpendicular distance from a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction and the X and Y values are perpendicular distances from the airfoil stacking line;a coating, said coating being applied over the nominal and uncoated shape; and wherein said coating has a thickness of between +0.002 and +0.014 inches. - View Dependent Claims (6)
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7. A turbine blade comprising:
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A coated airfoil profile, said profile having a shape formed by fairing a plurality of radial sections, said sections located within an envelope of between −
0.004 and +0.020 inches in any direction perpendicular to an airfoil stacking line, said stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches as listed in Table 1; andwherein R is a perpendicular distance from a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction and the X and Y values are perpendicular distances from the airfoil stacking line. - View Dependent Claims (8)
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Specification