Airfoil for a compressor blade

Patent metadata

Field	Value
Publication number	US-9291059-B2
Application number	US-64656109-A
Country	US
Kind code	B2
Filing date	Dec 23, 2009
Priority date	Dec 23, 2009
Publication date	Mar 22, 2016
Grant date	Mar 22, 2016

Abstract

The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD), stagger angle (γ) and camber angle (Δβ). The stagger angle (γ) and camber angle (Δβ) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.

First claim

What is claimed is:

1. An airfoil for a first stage compressor blade, the airfoil comprising:
a plurality of chord lengths, a plurality of stagger angles, and a plurality of camber angles at a plurality of divisions, respectively, along an airfoil height starting from a reference point at a first end of the airfoil of the first stage compressor blade extending to a second distal end of the airfoil of the first stage compressor blade, wherein for operation at a nominal frequency of 50 Hz:
at a first division starting from the reference point, the airfoil height is 0.000 mm, the stagger angle is 28.594 degrees, the chord length is 216.300 mm±10 millimeters, and the camber angle is 28.919 degrees±1 degree,
at a second division between the first division and the second distal end of the airfoil, the airfoil height is 72.059 mm±10 millimeters, the stagger angle is 35.305 degrees±1 degree, the chord length is 217.400 mm±10 millimeters, and the camber angle is 24.761 degrees±1 degree,
at a third division between the second division and the second distal end of the airfoil, the airfoil height is 139.669 mm±10 millimeters, the stagger angle is 40.998 degrees±1 degree, the chord length is 218.800 mm±10 millimeters, and the camber angle is 21.093 degrees±1 degree,
at a fourth division between the third division and the second distal end of the airfoil, the airfoil height is 203.900 mm±10 millimeters, the stagger angle is 45.857 degrees±1 degree, the chord length is 220.300 mm, and the camber angle is 17.883 degrees±1 degree,
at a fifth division between the fourth division and the second distal end of the airfoil, the airfoil height is 265.358 mm±10 millimeters, the stagger angle is 50.003 degrees±1 degree, the chord length is 222.000 mm, and the camber angle is 15.100 degrees±1 degree,
at a sixth division between the fifth division and the second distal end of the airfoil, the airfoil height is 324.430 mm±10 millimeters, the stagger angle is 53.520 degrees, the chord length is 223.900 mm, and the camber angle is 12.714 degrees,
at a seventh division between the sixth division and the second distal end of the airfoil, the airfoil height is 381.390 mm±10 millimeters, the stagger angle is 56.478 degrees±1 degree, the chord length is 225.800 mm, and the camber angle is 10.695 degrees±1 degree,
at an eighth division between the seventh division and the second distal end of the airfoil, the airfoil height is 436.490 mm±10 millimeters, the stagger angle is 58.932 degrees±1 degree, the chord length is 227.900 mm, and the camber angle is 9.014 degrees±1 degree, and
at a ninth division between the eighth division and the second distal end of the airfoil, the airfoil height is 489.880 mm, the stagger angle is 60.928 degrees, the chord length is 230.000 mm, and the camber angle is 7.644 degrees±1 degree, and
wherein for operation at a nominal frequency of 60 Hz measurements the airfoil height is scaled by a factor of 1:1.2.

2. The airfoil of claim 1 , wherein the values of the airfoil height, stagger angle, chord length and camber angle are carried to three decimal places.

3. An airfoil for a first stage compressor blade, comprising:
a plurality of chord lengths, a plurality of stagger angles, and a plurality of camber angles at a plurality of divisions, respectively, along an airfoil height starting from a reference point at a first end of the airfoil of the first stage compressor blade extending to a second distal end of the airfoil of the first stage compressor blade, wherein for operation at nominal frequency of 50 Hz:
at a first division starting from the reference point, the airfoil height is approximately 0.000 mm, the stagger angle is 28.594 degrees, the chord length is approximately 216.300 mm, and the camber angle is approximately 28.919 degrees,
at a second division between the first division and the second distal end of the airfoil, the airfoil height is approximately 72.059 mm, the stagger angle is approximately 35.305 degrees, the chord length is approximately 217.400 mm, and the camber angle is approximately 24.761 degrees,
at a third division between the second division and the second distal end of the airfoil, the airfoil height is approximately 139.669 mm, the stagger angle is approximately 40.998 degrees, the chord length is approximately 218.800 mm, and the camber angle is approximately 21.093 degrees,
at a fourth division between the third division and the second distal end of the airfoil, the airfoil height is approximately 203.900 mm, the stagger angle is approximately 45.857 degrees, the chord length is approximately 220.300 mm, and the camber angle is approximately 17.883 degrees,
at a fifth division between the fourth division and the second distal end of the airfoil, the airfoil height is approximately 265.358 mm, the stagger angle is approximately 50.003 degrees, the chord length is approximately 222.000 mm, and the camber angle is approximately 15.100 degrees,
at a sixth division between the fifth division and the second distal end of the airfoil, the airfoil height is approximately 324.430 mm, the stagger angle is approximately 53.520 degrees, the chord length is approximately 223.900 mm, and the camber angle is approximately 12.714 degrees,
at a seventh division between the sixth division and the second distal end of the airfoil, the airfoil height is approximately 381.390 mm, the stagger angle is approximately 56.478 degrees, the chord length is approximately 225.800 mm, and the camber angle is approximately 10.695 degrees,
at an eighth division between the seventh division and the second distal end of the airfoil, the airfoil height is approximately 436.490 mm, the stagger angle is approximately 58.932 degrees, the chord length is approximately 227.900 mm, and the camber angle is approximately 9.014 degrees, and
at a ninth division between the eighth division and the second distal end of the airfoil, the airfoil height is approximately 489.880 mm, the stagger angle is approximately 60.928 degrees, the chord length is approximately 230.000 mm, and the camber angle is approximately 7.644 degrees,
wherein the approximation of air foil height for the second through ninth divisions is within a range of±10 millimeters, the approximation of chord length for the first through ninth divisions is within a range of±10 millimeters, and the approximation of camber angle and stagger angle for the first through ninth divisions is within±1 degree,
wherein for operation at a nominal frequency of 60 Hz the airfoil height is scaled by a factor of 1:1.2.

Assignees

• Micheli Marco
• Dunkel Gabriel
• Puerta Luis Frederico
• Kappis Wolfgang
• Alstom Technology Ltd

Inventors

• Micheli Marco
• Dunkel Gabriel
• Puerta Luis Frederico
• Kappis Wolfgang

Classifications

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F04D29/324

  Blades · CPC title

• F05D2250/70

  Shape · CPC title