Airfoil shape for second stage compressor rotor blade
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.
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, and the Cartesian coordinate values of X, Y, and Z are defined relative to an origin point at a base of the airfoil.
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 the 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 the 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 10 percent of the airfoil length.
9. The system of claim 1 , wherein the first portion length is equal to or greater than 25 percent of the airfoil length.
10. The system of claim 1 , wherein the first portion length is equal to or greater than 50 percent of the airfoil length.
11. The system of claim 1 , wherein the first portion length is equal to or greater than 75 percent of the airfoil length.
12. The system of claim 1 , wherein the first portion length is equal to 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 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 a second stage compressor airfoil.
20. The system of claim 19 , wherein the airfoil is a compressor rotor blade.
21. The system of claim 1 , wherein the airfoil comprises the first suction portion of the 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 four decimal places.
22. The system of claim 1 , wherein the airfoil comprises the first suction portion of the 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 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, and the Cartesian coordinate values of X, Y, and Z are defined relative to an origin point at a base of the airfoil.
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, and the Cartesian coordinate values of X, Y, and Z are defined relative to an origin point at a base of the airfoil.