Airfoil profile with optimized aerodynamic shape

• US 20060024168A1
• Filed: 07/30/2004
• Published: 02/02/2006
• Est. Priority Date: 07/30/2004
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Magge, Shankar S., Fukuda, Takao, Price, Francis R.
• Granted Patent: US 7,094,034 B2
• Time in Patent Office: Days
• US Class Current: 416/223.R
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F05D 2220/3212 the first stage of a turbine
• CPC Class Codes: F05D 2240/301 Cross-sectional characteristics
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates
• CPC Class Codes: Y10S 416/02 Formulas of curves
• CPC Class Codes: Y10S 416/05 Variable camber or chord length

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.

Claims

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.

2. The aerodynamic profile of claim 1:

wherein each of said X, Y, and R coordinates are scaled by a positive value.

3. A gas turbine blade comprising:

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; 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.

4. The gas turbine blade of claim 3:

wherein said blade is a first stage turbine blade.

5. An aerodynamic profile for an airfoil, comprising:

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.

6. The aerodynamic profile of claim 5:

wherein each of said X, Y, and R coordinates are scaled by a positive value.

7. A turbine blade comprising:

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; 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.