Compressor blade
View Patent ↗A compressor component having an improved airfoil profile so as to eliminate previously known vibratory issues in the blade tip is disclosed. By altering the airfoil profile throughout its span, the natural frequency of the airfoil is altered so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1.
1. A compressor component comprising:
an attachment for securing the compressor component to a disk; and,
an airfoil extending radially outward from the attachment, the airfoil having a leading edge and a trailing edge with the trailing edge spaced a distance from the leading edge and separated by concave and convex surfaces;
wherein the airfoil has an uncoated profile substantially in accordance with Cartesian coordinate values of Table 1 having a set of X, Y, and Z coordinates, where the Y coordinate extends in a radially outward direction.
2. The compressor component of claim 1 , wherein the airfoil is solid.
3. The compressor component of claim 1 , wherein the compressor component is a rotating compressor blade.
4. The compressor component of claim 1 , wherein the coordinate values of Table 1 are measured relative to a center plane datum located approximately 0.205 inches from a bottom surface of the attachment.
5. The compressor component of claim 1 , wherein the airfoil and attachment are fabricated from a stainless steel alloy.
6. The compressor component of claim 1 further comprising a corrosion resistant coating applied to the airfoil.
7. The compressor component of claim 1 , wherein the airfoil has a surface profile of approximately +/− 0.008 inches from nominal.
8. The compressor component of claim 1 , wherein the airfoil is scalable by a factor of approximately 0.8-1.2.
9. A rotating compressor blade comprising:
an attachment having at least one contact surface for mating with a blade disk; and,
an airfoil extending radially outward from the attachment, 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, wherein Y is a distance measured radially outward from a datum plane extending through the attachment, 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.
10. The rotating compressor blade of claim 9 further comprising a corrosion resistant coating applied to the airfoil.
11. The rotating compressor blade of claim 10 , wherein the coating is applied approximately 0.001-0.003 inches thick.
12. The rotating compressor blade of claim 9 , wherein the airfoil can be scaled by a factor ranging from approximately 0.8-1.2 such that the blade can be utilized in alternate size engines.
13. The rotating compressor blade of claim 9 , wherein a concave surface and convex surface each extend radially outward to a generally planar tip of the blade.
14. The rotating compressor blade of claim 13 , wherein each of the concave and convex surfaces have a surface profile of approximately +/−0.008 inches from nominal.
15. The rotating compressor blade of claim 9 , wherein the Y coordinate values are measured a distance approximately 0.205 inches from a bottom surface of the attachment.
16. An airfoil for a compressor component 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, wherein Y is a distance measured radially outward from a center datum plane extending longitudinally through an attachment, 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.
17. The airfoil of claim 16 having manufacturing tolerances of approximately +/−0.004 inches.
18. The airfoil of claim 17 further comprising a coating applied to at least a portion of the airfoil, the coating having a thickness of approximately 0.001-0.003 inches.
19. The airfoil of claim 16 , wherein the compressor component is a rotating blade.
20. The airfoil of claim 16 , wherein the airfoil sections can be scaled larger or smaller uniformly.