Second stage turbine blade
View Patent ↗A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form an airfoil shape. The X, Y, and Z distances may be scaled as a function of the same constant number and the X, Y, and Z distances lie within an envelope of approximately +/−0.032 inches in directions normal to the airfoil.
1. A turbine blade comprising:
a blade root;
a platform extending from the blade root;
an airfoil extending from the platform to a tip and having an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein the X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape; and,
a shroud extending from the airfoil tip.
2. The turbine blade of claim 1 forming a part of a second stage turbine of a gas turbine engine.
3. The turbine blade of claim 1 , wherein the airfoil has a height as measured from a midpoint of the platform to a tip of the airfoil of approximately 14.147 inches.
4. The turbine blade of claim 1 further comprising a coating applied to at least the airfoil.
5. The turbine blade of claim 1 , wherein the shroud further comprises a plurality of knife edges extending away from the shroud, opposite the airfoil.
6. The turbine blade of claim 1 , wherein the X, Y, and Z values are scalable as a function of one or more constants.
7. A turbine blade comprising:
a blade root;
a platform extending from the blade root;
an airfoil extending from the platform, the airfoil having an airfoil shape within an envelope of approximately −0.032 to +0.032 inches in a direction normal to any surface of the airfoil, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein the X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape, and,
a shroud extending from the airfoil tip.
8. The turbine blade of claim 7 forming a part of a second stage turbine of a gas turbine engine.
9. The turbine blade of claim 7 further comprising a coating applied to the airfoil.
10. The turbine blade of claim 7 , wherein the shroud further comprises a plurality of knife edges extending away from the shroud, opposite the airfoil.
11. The turbine blade of claim 7 , wherein the X, Y, and Z values are scalable as a function of one or more constants.
12. A turbine comprising:
a turbine wheel positioned along an engine centerline;
a plurality of turbine blades secured to the turbine wheel, each turbine blade comprising:
a blade root;
a platform extending radially outward from the blade root;
an airfoil extending radially outward from the platform, the airfoil having an airfoil tip and an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein the X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape; and,
a shroud extending from the airfoil tip.
13. The turbine of claim 12 forming a part of a second stage of a gas turbine engine.
14. The turbine of claim 12 , wherein the turbine blade further comprises a coating applied to at least the airfoil.
15. The turbine blade of claim 12 , wherein the shroud further comprises a plurality of knife edges extending away from the shroud, opposite the airfoil.
16. The turbine blade of claim 12 , wherein the X, Y, and Z values are scalable as a function of one or more constants.
17. A turbine comprising:
a turbine wheel positioned along an engine centerline;
a plurality of turbine blades secured to the turbine wheel, each turbine blade comprising:
a blade root;
a platform extending radially outward from the blade root;
an airfoil extending radially outward from the platform, the airfoil having an airfoil tip and an airfoil shape within an envelope of approximately −0.032 to +0.032 inches in a direction normal to any surface location of the airfoil, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein the X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape; and,
a shroud extending from the airfoil tip.
18. The turbine of claim 17 forming a part of a second stage of a gas turbine engine.
19. The turbine of claim 17 , wherein the turbine blade further comprises a coating applied to at least the airfoil.
20. The turbine blade of claim 17 , wherein the shroud further comprises a plurality of knife edges extending away from the shroud, opposite the airfoil.
21. The turbine blade of claim 17 , wherein the X, Y, and Z values are scalable as a function of one or more constants.