Airfoil shape for a turbine rotor blade

Patent metadata

Field	Value
Publication number	US-10422227-B2
Application number	US-201715584541-A
Country	US
Kind code	B2
Filing date	May 2, 2017
Priority date	May 2, 2017
Publication date	Sep 24, 2019
Grant date	Sep 24, 2019

Abstract

A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

First claim

What is claimed is:

1. A turbine rotor blade including an 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 I, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape, wherein the airfoil shape lies in an envelope within +/−5% in a direction normal to any airfoil surface location.

2. The turbine rotor blade as in claim 1 , forming part of a fourth stage of turbine rotor blades of a turbine of a gas turbine.

3. The turbine rotor blade as in claim 1 , wherein the turbine rotor blade includes a part-span shroud having a pressure-side shroud disposed along a pressure-side of the airfoil.

4. The turbine rotor blade as in claim 1 , wherein a height of the turbine rotor blade is 5 inches to 50 inches.

5. A turbine rotor blade including an airfoil having a suction-side uncoated nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in Table I, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance, the airfoil profile sections at the Z distances being joined smoothly with one another to form a complete suction-side airfoil shape, the X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil, wherein the suction-side airfoil shape lies in an envelope within +/−5% in a direction normal to any suction-side airfoil surface location.

6. The turbine rotor blade as in claim 5 , forming part of a stage of a turbine.

7. The turbine rotor blade as in claim 5 , wherein the turbine rotor blade forms a part of a fourth stage of turbine rotor blades of a turbine of a gas turbine.

8. The turbine rotor blade as in claim 5 , wherein a height of the turbine rotor blade is 5 inches to 50 inches.

9. The turbine rotor blade as in claim 5 , wherein the turbine rotor blade includes a part-span shroud having a suction-side shroud disposed along the suction-side of the airfoil.

10. A turbine comprising a turbine wheel having a plurality of turbine rotor blades, each of the turbine rotor blades including an airfoil having a suction-side airfoil shape, the airfoil having a nominal profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil, and wherein X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance, the airfoil profile sections at the Z distances being joined smoothly with one another to form a complete suction-side airfoil shape, wherein the suction-side airfoil shape lies in an envelope within +/−5% in a direction normal to any suction-side airfoil surface location.

11. The turbine as in claim 10 , wherein the turbine wheel comprises a stage of the turbine.

12. The turbine as in claim 10 , wherein X represents a distance parallel to the turbine axis of rotation.

13. The turbine as in claim 10 , wherein a height of the turbine rotor blade is 5 inches to 50 inches.

14. The turbine as in claim 10 , wherein each of the turbine rotor blades includes an airfoil having a pressure-side airfoil shape, the airfoil having a nominal profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y and Z set forth in Table I wherein the pressure-side Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the pressure-side Cartesian coordinate values of X, Y and Z by a height of the airfoil, and wherein X and Y are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape, wherein the airfoil shape lies in an envelope within +/−5% in a direction normal to any airfoil surface location.

15. The turbine as in claim 14 , wherein the turbine rotor blade is a fourth stage turbine rotor blade.

16. The turbine as in claim 14 , wherein X represents a distance parallel to the turbine axis of rotation.

Assignees

• Gen Electric

Inventors

• Bielek Craig Allen
• Taylor Zachary James
• Wells Charles Wesley

Classifications

• F01D5/143 Primary

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F01D5/141 Primary

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

• F05D2250/74

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

• F05D2240/301

  Cross-sectional characteristics · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title