Airfoil shape for eleventh stage compressor stator vane

Patent metadata

Field	Value
Publication number	US-10132330-B2
Application number	US-201615286556-A
Country	US
Kind code	B2
Filing date	Oct 5, 2016
Priority date	Oct 5, 2016
Publication date	Nov 20, 2018
Grant date	Nov 20, 2018

Abstract

A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

First claim

The invention claimed is:

1. A system comprising:
an airfoil comprising a first suction portion of a nominal airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil comprises an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

2. The system of claim 1 , wherein the airfoil comprises a second suction portion of the nominal airfoil profile in accordance with the Cartesian coordinate values of X, Y, and Z of the suction side as set forth in TABLE I to the maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the second suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the second suction portion of the nominal airfoil profile are coupled together to define the second suction portion, the second suction portion comprises a second portion length along the Z axis, the second portion length is less than or equal to the airfoil length, and the first and second suction portions are offset from one another along the Z axis.

3. The system of claim 1 , wherein the airfoil comprises a first pressure portion of the nominal airfoil profile in accordance with the Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in TABLE I to the maximum of three decimal places, wherein the X and Y values of the pressure side are coordinate values that couple together to define pressure side sections of the first pressure portion of the nominal airfoil profile at each Z coordinate value, the pressure side sections of the first pressure portion of the nominal airfoil profile are coupled together to define the first pressure portion, the first pressure portion comprises a second portion length along the Z axis, and the second portion length is less than or equal to the airfoil length.

4. The system of claim 3 , wherein the first suction portion and the first pressure portion at least partially overlap with one another along the Z axis.

5. The system of claim 4 , wherein the first and second portion lengths are the same, and the first and second portion lengths start at a common distance relative to a base of the airfoil and extend toward a tip of the airfoil.

6. The system of claim 1 , wherein the first portion length of the first suction portion starts at a distance relative to a base of the airfoil and extends toward a tip of the airfoil.

7. The system of claim 1 , wherein the first portion length includes greater than or equal to two consecutive Cartesian coordinate values of Z in TABLE I.

8. The system of claim 1 , wherein the first portion length is equal to or greater than approximately 10 percent of the airfoil length.

9. The system of claim 1 , wherein the first portion length is equal to or greater than approximately 25 percent of the airfoil length.

10. The system of claim 1 , wherein the first portion length is equal to or greater than approximately 50 percent of the airfoil length.

11. The system of claim 1 , wherein the first portion length is equal to or greater than approximately 75 percent of the airfoil length.

12. The system of claim 1 , wherein the first portion length is equal to approximately 100 percent of the airfoil length.

13. The system of claim 1 , wherein the airfoil comprises the nominal airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z as set forth in TABLE I to the maximum of three decimal places along an entirety of both the suction side and a pressure side of the airfoil.

14. The system of claim 1 , wherein the airfoil comprises a coating disposed over the first suction portion of the nominal airfoil profile in accordance with the Cartesian coordinate values of X, Y, and Z of the suction side as set forth in TABLE I to the maximum of three decimal places.

15. The system of claim 14 , wherein the coating increases the X and Y values of the suction side in TABLE I to the maximum of three decimal places by no greater than approximately 3.5 mm along the first suction portion.

16. The system of claim 1 , comprising a plurality of compressor airfoils of a compressor stage, wherein each of the plurality of compressor airfoils comprises the airfoil having the first suction portion of the nominal airfoil profile in accordance with the Cartesian coordinate values of X, Y, and Z of the suction side as set forth in TABLE I to the maximum of three decimal places.

17. The system of claim 1 , comprising a compressor having the airfoil.

18. The system of claim 17 , comprising a gas turbine engine having the compressor, a combustor, and a turbine.

19. The system of claim 1 , wherein the airfoil is an eleventh stage compressor airfoil.

20. The system of claim 19 , wherein the airfoil is a compressor stator vane.

21. The system of claim 1 , wherein the airfoil comprises the first suction portion of the nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of the suction side as set forth in TABLE I to a maximum of four decimal places.

22. The system of claim 1 , wherein the airfoil comprises the first suction portion of the nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of the suction side as set forth in TABLE I to a maximum of five decimal places.

23. A system comprising:
an airfoil comprising a suction side of a nominal airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z of the suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the suction side of the nominal airfoil profile at each Z coordinate value, the suction side sections of the suction side of the nominal airfoil profile are coupled together to define the suction side, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

24. A system comprising:
an airfoil comprising a nominal airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values are coordinate values that couple together to define airfoil sections of the nominal airfoil profile at each Z coordinate value, the airfoil sections of the nominal airfoil profile are coupled together to define an entirety of the airfoil, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Assignees

• Gen Electric

Inventors

• Modachur Krishnan Prabakaran
• Davidson Dwight Eric

Classifications

• F05D2240/305

  related to the pressure side of a rotor blade · CPC title

• F04D29/324

  Blades · CPC title

• F05D2220/3216

  for a special compressor stage · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D5/141

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