First stage turbine blade
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 and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
1. A turbine blade comprising:
a blade root;
a platform extending from the blade root; and,
an airfoil extending from the platform, the airfoil 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.
2. The turbine blade of claim 1 forming a part of a first stage turbine of a gas turbine engine.
3. : The turbine blade of claim 1 , wherein the turbine blade has an airfoil height measured from a midpoint of the platform to a tip of the airfoil being 7.3 inches.
4. The turbine blade of claim 1 further comprising a coating applied to the airfoil.
5. The turbine blade of claim 1 , wherein an orientation of the airfoil is rotatable about an axis extending along the Z values.
6. The turbine blade of claim 1 , wherein the X and Y values are scalable by a first constant and the Z values are scalable by a second constant.
7. : A turbine blade comprising: a blade root; a platform extending from the blade root; and, an airfoil extending from the platform, the airfoil having an airfoil shape within an envelope of −0.033 to +0.033 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.
8. The turbine blade of claim 7 forming a part of a first stage turbine of a gas turbine engine.
9. : The turbine blade of claim 7 , wherein the turbine blade has an airfoil height measured from a midpoint of the platform to a tip of the airfoil being 7.3 inches.
10. The turbine blade of claim 7 further comprising a coating applied to the airfoil.
11. The turbine blade of claim 7 , wherein the X and Y values are scalable by a first constant and the Z values are scalable by a second constant.
12. The turbine blade of claim 7 , wherein an orientation of the airfoil is rotatable about an axis extending along the Z values.
13. 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; and,
an airfoil extending radially outward from the platform, the airfoil 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.
14. The turbine of claim 13 forming a part of a first stage of a gas turbine engine.
15. The turbine of claim 13 , wherein the turbine blade has an airfoil height measured from a midpoint of the platform to a tip of the airfoil being 7.3 inches.
16. The turbine of claim 13 , wherein the turbine blade further comprises a coating applied to the airfoil.
17. The turbine blade of claim 13 , wherein an orientation of the airfoil is rotatable about an axis extending along the Z values.
18. The turbine blade of claim 13 , wherein the X and Y values are scalable by a first constant and the Z values are scalable by a second constant.
19. : 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 from the blade root; and, an airfoil extending from the platform, the airfoil having an airfoil shape within an envelope of −0.033 to +0.033 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.
20. The turbine of claim 19 forming a part of a first stage of a gas turbine engine.
21. The turbine of claim 19 , wherein the turbine blade has an airfoil height measured from a midpoint of the platform to a tip of the airfoil being 7.3 inches.
22. The turbine of claim 19 , wherein the turbine blade further comprises a coating applied to the airfoil.
23. The turbine blade of claim 19 , wherein an orientation of the airfoil is rotatable about an axis extending along the Z values.
24. The turbine blade of claim 19 , wherein the X and Y values are scalable by a first constant and the Z values are scalable by a second constant.