First stage turbine blade

Patent metadata

Field	Value
Publication number	US-10711615-B2
Application number	US-201816107363-A
Country	US
Kind code	B2
Filing date	Aug 21, 2018
Priority date	Aug 21, 2018
Publication date	Jul 14, 2020
Grant date	Jul 14, 2020

Abstract

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.

First claim

Having thus described the invention, what is claimed is:

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.

Assignees

• Chromalloy Gas Turbine Llc

Inventors

• Parker David G
• Xiao Zhenhua
• Yu Richard
• Martling Vincent C
• Smith Wesley
• Medrano David
• Ellis Charles A

Classifications

• F01D5/141 Primary

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

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F01D5/288

  Protective coatings for blades · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title