COMPRESSOR BLADE FOR A GAS TURBINE ENGINE

• US 20180017077A1
• Filed: 07/12/2016
• Published: 01/18/2018
• Est. Priority Date: 07/12/2016
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: DeIvernois, Paul Griffin, Rivard, Kenneth Paul
• Granted Patent: US 10,273,975 B2
• Time in Patent Office: Days
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F05B 2220/302 in gas turbines
• CPC Class Codes: F05B 2250/70 Shape
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates

Abstract

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Claims

1. An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

2. The article of manufacture according to claim 1, wherein the article of manufacture comprises an airfoil configured for use with a compressor.

3. The article of manufacture according to claim 1, wherein the article of manufacture comprises a stator vane configured for use with a compressor.

4. The article of manufacture according to claim 1, wherein the airfoil shape lies in an envelope within one of:

+/−

5% of a chord length in a direction normal to an airfoil surface location; and

+/−

0.25 inches in a direction normal to an airfoil surface location.

5. The article of manufacture according to claim 1, wherein the number, used to convert the non-dimensional values to dimensional distances, is one of a fraction, decimal fraction, integer and mixed number.

6. The article of manufacture according to claim 1, wherein a height of the article of manufacture is about 1 inch to about 20 inches.

7. An article of manufacture having a suction-side nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape, the X, Y and Z coordinate values being scalable as a function of the number to provide one of a non-scaled, scaled-up and scaled-down airfoil profile.

8. The article of manufacture according to claim 7, wherein the article of manufacture comprises an airfoil configured for use with a compressor.

9. The article of manufacture according to claim 7, wherein the article of manufacture comprises a stator vane configured for use with a compressor.

10. The article of manufacture according to claim 7, wherein the suction-side airfoil shape lies in an envelope within one of:

+/−

5% of a chord length in a direction normal to a suction-side airfoil surface location; and

+/−

0.25 inches in a direction normal to a suction-side airfoil surface location.

11. The article of manufacture according to claim 7, wherein the number, used to convert the non-dimensional values to dimensional distances, is one of a fraction, decimal fraction, integer and mixed number.

12. The article of manufacture according to claim 7, wherein a height of the article of manufacture is about 1 inch to about 20 inches.

13. The article of manufacture according to claim 7, further comprising the article of manufacture having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y and Z set forth in the scalable table, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by the number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape, the X, Y and Z values being scalable as a function of the number to provide one of a non-scaled, scaled-up and scaled-down airfoil.

14. A compressor comprising a plurality of stator vanes, each of the stator vanes including an airfoil having a suction-side airfoil shape, the airfoil having a nominal profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape.

15. The compressor according to claim 14, wherein the suction-side airfoil shape lies in an envelope within one of:

+/−

5% of a chord length in a direction normal to a suction-side airfoil surface location; and

+/−

0.25 inches in a direction normal to a suction-side airfoil surface location.

16. The compressor according to claim 14, wherein the number, used to convert the non-dimensional values to dimensional distances, is one of a fraction, decimal fraction, integer and mixed number.

17. The compressor according to claim 14, wherein a height of each stator vane is about 1 inch to about 20 inches.

18. The compressor according to claim 14, further comprising each of the plurality of stator vanes having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y and Z set forth in the scalable table, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by the number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape.

19. The compressor according to claim 18, wherein the pressure-side airfoil shape lies in an envelope within one of:

+/−

5% of a chord length in a direction normal to a pressure-side airfoil surface location; and

+/−

0.25 inches in a direction normal to a pressure-side airfoil surface location.

20. The compressor according to claim 18, wherein the number, used to convert the non-dimensional values to dimensional distances, is one of a fraction, decimal fraction, integer and mixed number.